REM press F5 REM DEVELOP A REQUIREMENTS SPECIFICATION CLS PI = 3.141592 DEFSNG A-Z SS = 1 SCREEN 1: VIEW (10, 10)-(300, 180), , 4 COLOR 1 LOCATE 5, 4: PRINT " THIS PROGRAM IS DESIGNED FOR " LOCATE 7, 4: PRINT " THE CALCULATION OF LIGHT ONE AND DOUBLE SEAT " LOCATE 9, 4: PRINT " AIRCRAFT WEIGHING LESS THAN " LOCATE 11, 4: PRINT " 580 KG AND the ENGINE TO 140 HP" LOCATE 13, 5: PRINT " YOU WILL BE ABLE TO CALCULATE TAKE-OFF WEIGHT " LOCATE 15, 6: PRINT " OF THE AIRCRAFT DESIGNED," LOCATE 17, 6: PRINT " AERODYNAMIC AND LANDING CHARACTERISTICS, " LOCATE 19, 7: PRINT " TO OPTIMIZE ITS PARAMETERS " LOCATE 21, 6: PRINT " ... " SLEEP 7 CLS COLOR 1 SCREEN 1: VIEW (10, 10)-(300, 180), , 4 LOCATE 12, 9: PRINT " DEVELOP A REQUIREMENTS SPECIFICATION" SLEEP 2 1 CLS: SCREEN 12: COLOR 3 LOCATE 1, 29: PRINT " DEVELOP A REQUIREMENTS SPECIFICATION" LOCATE 3, 1: PRINT " REQUIREMENTS / TYPE AMATEUR PATROL FLIGHT TRAINING" LOCATE 4, 1: PRINT " Crew 1 1+1 side by side 1 1+1 tandem" LOCATE 5, 1: PRINT " Loading , Ny +3;-1.5 +4;-2 +8;-8 +6;-3" LOCATE 6, 1: PRINT " FLIGHT RANGE 200 KM 500 KM 300 KM 400 KM " LOCATE 7, 1: PRINT " FLIGHT TIME ,HRS. 1-2 >3 1 2" LOCATE 8, 1: PRINT " CRUISE SPEED 90-150 KM/H 100-150 KM/H 250-300 KM/H 130-200 KM/H " LOCATE 9, 1: PRINT " LANDING SPEED < 70 KM/H 60 KM/H 95 KM/H 70 KM/H " LOCATE 10, 1: PRINT " MANEUVERABILITY ++ + +++ ++" LOCATE 11, 1: PRINT " ENGINE POWER 35-60 HP 60-100 HP 200-300 HP 60-150 HP" LOCATE 12, 1: PRINT " FLIGHT WEIGHT ,KG. <300 450 500-800 480 " LOCATE 13, 1: PRINT " THE SCHEME OF THE AIRFRAME ANY HIGH WING MIDDLE WING ANY " LOCATE 16, 1: PRINT "IN THE TERMS OF REFERENCE ARE DETERMINED BY THE PURPOSE FOR WHICH IT IS PLANNED TO USE THE AIRCRAFT" LOCATE 17, 15: PRINT " AS WELL AS THE INTENDED ENGINE." LOCATE 18, 1: PRINT "ALSO DETERMINED BY THE TAKEOFF AND LANDING PERFORMANCE" LOCATE 19, 1: PRINT "AND OTHER REQUIRED PERFORMANCE CHARACTERISTICS," LOCATE 20, 1: PRINT " STRENGTH REQUIREMENTS , LAYOUT AND EQUIPMENT , USEFUL LIFE , COST , COST PER FLIGHT HOUR AND SO ON." PRINT PRINT INPUT "eNTER Ny = ", NY INPUT "SCHEME: PARASOL -1; HIGH WING -2; MIDDLEWING -3; BIPLANE -4; LOW WING -5 ", FAF IF NY <= 4 THEN KM = 5 IF NY > 4 AND NY <= 6 THEN KM = 7 IF NY > 6 THEN KM = 9 NR = NY * 1.5: CLS SCREEN 1: VIEW (10, 10)-(300, 180), , 4: COLOR 1 LOCATE 10, 8: PRINT " CALCULATING" LOCATE 10, 22: PRINT " FLIGHT " LOCATE 14, 12: PRINT " WEIGHT " LOCATE 14, 18: PRINT " OF AIRCRAFT" SLEEP 2: CLS: SCREEN 12: COLOR 3 PRINT " TAKEOFF WEIGHT IN FIRST APPROACH" PRINT PRINT " TAKEOFF WEIGHT IN FIRST APPROACH TAKES FROM STATISTICS" PRINT " OR FROM PROTOTYPE " PRINT PRINT " OR IS CALCULATED BY THE KNOWN RELATIVE MASSES OF THE PARTS COLLECTED ON" PRINT " THE BASIS OF THE STATISTICAL ANALYSIS FOR THIS TYPE OF AIRCRAFT" PRINT PRINT "THUS, THE RELATIVE WEIGHT OF THE WING IS APPROXIMATELY=0.15-0.2 TAKE-OFF WEIGHT" PRINT " THE RELATIVE MASS OF FUSELAGE =0.14-0.2 " PRINT " THE RELATIVE WEIGHT OF THE TAIL =0.04-0.05 " PRINT " THE RELATIVE MASS OF POWER PLANT =0.1-0.2 " PRINT " THE RELATIVE WEIGHT OF CHASSIS=0.05-0.08 " PRINT " THE RELATIVE WEIGHT OF THE CONTROL AND EQUIPMENT =0.03-0.1 " PRINT " THE RELATIVE MASS OF THE FUEL =0.05-0.1 " PRINT PRINT " THE PAYLOAD MASS INCLUDES THE WEIGHT OF THE RIDER , LUGGAGE AND SO ON " PRINT " THE MASS OF THE PILOT 80 KG , PARACHUTE PLP-60 - 9 KG" PRINT PRINT PRINT INPUT " ENTER THE WEIGHT OF THE FIRST APPROXIMATION , KG = ", GS1 LOCATE 26, 1: PRINT "******************** !!!!!!! ************************" SLEEP 2 200 CLS: SCREEN 12: COLOR 3 PRINT " MASS II APPROXIMATION" PRINT PRINT " THE CALCULATION IS MADE AFTER THE DRAWING OF GENERAL ARRANGEMENT DRAWING OF THE AIRCRAFT " PRINT " THE PURPOSE OF THIS STAGE OF CALCULATION IS MORE ACCURATE DETERMINATION OF THE MASSES" PRINT " OF THE INDIVIDUAL PARTS AND THE ENTIRE PLANE AS A WHOLE " PRINT PRINT " feature of the CALCULATION IS considering the relationship of the MASSES of the INDIVIDUAL PARTS FROM" PRINT " the take-off MASS M1 , the ESTIMATED OVERLOAD Nr the SIZE of the AIRCRAFT" PRINT " THE CALCULATION IS BASED ON EMPIRICAL FORMULAS " PRINT 2 PRINT " WING " PRINT INPUT " THE MAIN MATERIAL OF THE WING: COMPOZITS - 1; ALUMINIUM - 2; WOOD - 3 ", KK IF KK = 1 THEN KKK = .7 IF KK = 2 THEN KKK = .8 IF KK = 3 THEN KKK = 1 INPUT " WING AREA , M2 ", SK INPUT " WING SPAN , M ", RK INPUT " WING CHORD , M ", XK IF SE > 1 THEN GOTO 9 INPUT " WING : CANTILEVER - 0 ;STRUT-BRACED WING - 1 ;WITH BRACES - 2 ", PKK IF PKK = 1 THEN INPUT " ENTER STRUTS QUONTITY FOR ONE HALF OF THE WING ", NPO IF PKK = 1 THEN INPUT " STRUT PROFILE : CIRCLE -0 ; OVAL -1 ; DROP -2 ", SPO IF PKK = 2 THEN INPUT " ENTER BRACES QUONTITY FOR ONE HALF OF THE WING ", NPO LPOD = RK / 2 * .6: KOP = NPO * 2 IF PKK = 1 THEN MP = LPOD * KOP * .6 IF PKK = 2 THEN MP = LPOD * KOP * .061 MKT = .002 * KKK * GS1 * NR * (.6 * ((RK / 2) ^ 2) + 1) + 3 * SK IF PKK = 1 THEN MK2 = MKT * .7 + MP IF PKK = 0 THEN MK2 = MKT IF PKK = 2 THEN MK2 = MKT * .7 + MP PRINT PRINT " WING MASS II APPROXIMATION, KG =", MK2 PRINT PRINT INPUT " ENTER FUEL WEIGHT , kg ", MAT CLS PRINT " MASS II APPROXIMATION" PRINT INPUT " FUSELAGE : BULK - 1 ; FLAT FARM, OR THIN BEAM - 2 ", FOF INPUT " ENTER FUSELAGE LENTH, M = ", LF INPUT " ENTER FUSELAGE HEIGHT , M = ", HF INPUT " MAXIMAL WIDTH OF FUSELAGE , M = ", SF 3 PRINT INPUT " THE CANOPY : OPEN CABIN WITH CANOPY(TIGER MOTH) - 1 HEMISPHERICAL SHAPE CANOPY ( 2-SEATER )(CH 601) - 2 CANOPY WITH FLAT FACES AND SHORT FAIRING (THE YAK-18U)- 3 FLAT FRONT,BLENDING SMOOTHLY INTO THE TAIL (YAK-12A)- 4 ROUNDED FRONT , LONG FAIRING( Z-50L) - 5 CANOPY FADES INTO THE TAIL (YAK-18T)- 6 A STREAMLINED GLIDER (LAMINAR) FUSELAGE - 7 ", KOF SM = SF * HF 'THE AREA OF THE MIDSECTION ( RECTANGLE )' IF GS1 < 350 THEN VA = 11 IF GS1 >= 350 THEN VA = 15 MF2 = 2.5 * 2.85 * LF * SQR(SM) + VA PRINT PRINT " MASS OF FUSELAGE, KG =", MF2 PRINT SLEEP 1 PRINT " TAIL" PRINT INPUT " ENTER HORIZONTAL TAIL AREA, M2 = ", SGO INPUT " ENTER VERTICAL TAIL AREA, M2 = ", SVO INPUT " MAIN TAIL MATERIAL : COMPOSITS - 1 ; ALUMINIUM - 2 ; WOOD - 3 - ", KOK INPUT " TAIL : CANTILEVER - 0 ;STRUT-BRACED WING - 1 ;WITH BRACES - 2 - ", PGO SO = SVO + SGO IF KOK = 1 THEN MOK = .7 IF KOK = 2 THEN MOK = .8 ' COEF OF MATERIAL' IF KOK = 3 THEN MOK = 1 MO = .64 * MOK * ((NR * SO ^ 2)) ^ .75 IF PGO = 1 OR PGO = 2 THEN MO = MO * .8 PRINT PRINT PRINT " TAIL MASS II APPROXIMATION, kg =", MO SLEEP 2: CLS PRINT " MASS II APPROXIMATION" PRINT PRINT " POWER PLANT " PRINT INPUT "ENGINE: RMZ-640 -1; R-447 - 2; R-503 - 3; R-532 - 4; HIRTH-2706 -5; HIRTH F 30 -6; R-912 UL -7; KONIG SF 930 -8; LIMBACH SL 1700E -9; STAMO MS 1500 -10; VALTER 332 -12; OTHER -11; NO ENGINE -0 ", NN REM SU - ENGINE + REDUCTOR + PROPELLER REM ND - POWER, HP IF NN = 1 THEN SU = 52: ND = 35: NO = 5500: NOR = 2900: NOS = 91.6: NORS = 48.3: F$ = "RMZ-640": FI$ = "35 HP": N$ = "5500 ": NR$ = "2900 " IF NN = 2 THEN SU = 41: ND = 43: NO = 6500: NOR = 2901: NOS = 108.3: NORS = 48.35: F$ = "R-447-2V": FI$ = "43 HP": N$ = "6500 ": NR$ = "2901 " IF NN = 3 THEN SU = 46: ND = 50: NO = 6500: NOR = 2901: NOS = 108.3: NORS = 48.35: F$ = "R-503-2V": FI$ = "50 HP": N$ = "6500": NR$ = "2901" IF NN = 4 THEN SU = 45: ND = 64: NO = 6500: NOR = 2901: NOS = 108.3: NORS = 48.35: F$ = "R-532-2V": FI$ = "64 HP": N$ = "6500 ": NR$ = "2901 " IF NN = 5 THEN SU = 46: ND = 65: NO = 6100: NOR = 2723: NOS = 101.6: NORS = 45.38: F$ = "HIRTH-2706": FI$ = "65 HP": N$ = "6100": NR$ = "2723" IF NN = 6 THEN SU = 45: ND = 65: NO = 5700: NOR = 2850: NOS = 95: NORS = 47.5: F$ = "HIRTH F 30": FI$ = "65 HP": N$ = "5700 ": NR$ = "2850" IF NN = 7 THEN SU = 68: ND = 80: NO = 5500: NOR = 2750: NOS = 91.6: NORS = 45.83: F$ = "R-912 UL": FI$ = "80 HP": N$ = "5500 ": NR$ = "2750 " IF NN = 8 THEN SU = 40: ND = 48: NO = 4200: NOR = 2100: NOS = 70: NORS = 35: F$ = "KONIG 930": FI$ = "48 HP": N$ = "4200 ": NR$ = "2100" IF NN = 9 THEN SU = 78: ND = 68: NO = 3600: NOR = 2400: NOS = 60: NORS = 40: F$ = "LIMBACH SL": FI$ = "68 HP": N$ = "3600 ": NR$ = "2400 " IF NN = 10 THEN SU = 64: ND = 45: NO = 3600: NOR = 2400: NOS = 60: NORS = 40: F$ = "STAMO 1500": FI$ = "45 HP": N$ = "3600 ": NR$ = " 2400 " IF NN = 12 THEN SU = 100: ND = 140: NOR = 2500: NORS = 41.6: F$ = "VALTER M332": FI$ = "140 HP": NR$ = "2500 " IF NN = 0 THEN GOTO 5 IF NN = 11 THEN GOTO 46 4 PRINT INPUT "ENGINE PLACEMENT: FRONT - 1, REAR - 2- 2 ", RD INPUT "IS ENGINE COVERED ? Y - 1 ; N - 0 ; IN FUZELAGE - 2 ", DVZ PRINT PRINT "MASS OF POWER PLANT, KG ", SU 5 PRINT GOTO 47 46 CLS PRINT " MASS II APPROXIMATION " PRINT PRINT " POWER PLANT " PRINT INPUT "ENTER ENGIN POWER, HP ", ND INPUT "ENTER THE REVOLUTIONS OF THE SCREW , REV/MIN", NOR NORS = NOR / 60 NOS = NORS INPUT "ENTER POWER PLANT MASS , KG ", SU F$ = "ORIGINAL": FI$ = "*": NR$ = "*" PRINT INPUT "ENGINE PLACEMENT: FRONT - 1, REAR - 2- 2 ", RD INPUT "IS ENGINE COVERED ? Y - 1 ; N - 0 ; IN FUZELAGE - 2", DVZ PRINT PRINT 47 SLEEP 1 PRINT " CHASSIS " PRINT INPUT "CHASSIS TYPE : PYRAMIDAL -1; PLASTIC SPRING -2 STEEL SPRING -3 STEEL TUBE -3 ", SHA INPUT "PNEUMATIC : 200*80 - 1 ; 300*125 - 2 ; 400*150 -3 ; FROM CARTING - 4 ", PNE INPUT "SCHEME : WITH THE FRONT PILLAR 1 ; WITH BACK SUPPORT - 2 ", OPO INPUT "CHASSIS : THE RETRACTABLE IN - FLIGHT 1 ; FIXED - 0 ", US REM MH - CHASSIS MASS; SMS,SMP - THE AREA OF THE MIDSECTION ; CXO - COEF IF SHA = 1 AND OPO = 2 AND GS1 <= 300 THEN MH = 7: SMS = .068 IF SHA = 2 AND OPO = 2 AND GS1 <= 300 THEN MH = 9: SMS = .032 IF SHA = 3 AND OPO = 2 AND GS1 <= 300 THEN MH = 11: SMS = .0187 IF SHA = 1 AND OPO = 2 AND GS1 > 300 THEN MH = 10: SMS = .102 IF SHA = 2 AND OPO = 2 AND GS1 > 300 THEN MH = 13: SMS = .04 IF SHA = 3 AND OPO = 2 AND GS1 > 300 THEN MH = 16: SMS = .04 IF SHA = 1 AND OPO = 1 AND GS1 <= 300 THEN MH = 9: SMS = .068 + .012 IF SHA = 2 AND OPO = 1 AND GS1 <= 300 THEN MH = 11: SMS = .032 + .012 IF SHA = 3 AND OPO = 1 AND GS1 <= 300 THEN MH = 13: SMS = .0187 + .012 IF SHA = 1 AND OPO = 1 AND GS1 > 300 THEN MH = 12: SMS = .102 + .016 IF SHA = 2 AND OPO = 1 AND GS1 > 300 THEN MH = 15: SMS = .04 + .016 IF SHA = 3 AND OPO = 1 AND GS1 > 300 THEN MH = 18: SMS = .04 + .016 IF SHA = 4 AND OPO = 1 AND GS1 > 300 THEN MH = 8: SMS = .048 IF SHA = 4 AND OPO = 1 AND GSI <= 300 THEN MH = 6: SMS = .048 IF SHA = 4 AND OPO = 2 AND GS1 > 300 THEN MH = 6: SMS = .032 IF SHA = 4 AND OPO = 2 AND GS1 <= 300 THEN MH = 4: SMS = .032 IF PNE = 1 AND OPO = 1 THEN MAP = 9: SMP = .014624: CXP = .25 IF PNE = 1 AND OPO = 2 THEN MAP = 6: SMP = .014624: CXP = .25 IF PNE = 2 AND OPO = 1 THEN MAP = 10.5: SMP = .03414: CXP = .25 IF PNE = 2 AND OPO = 2 THEN MAP = 7: SMP = .03414: CXP = .25 IF PNE = 3 AND OPO = 1 THEN MAP = 12: SMP = .0551625: CXP = .25 IF PNE = 3 AND OPO = 2 THEN MAP = 8: SMP = .0551625: CXP = .25 IF PNE = 4 AND OPO = 1 THEN MAP = 9: SMP = .0375: CXP = .5 IF PNE = 4 AND OPO = 2 THEN MAP = 6: SMP = .0375: CXP = .5 IF US = 1 THEN MH = MH * 1.25 MAS = MH + MAP REM DRUG RATIO OF MAIN AND FRONT CHASSIS STRUTS CXOS = 1 IF OPO = 1 THEN SUM = SMS + (3 * SMP * CXP) IF OPO = 2 THEN SUM = SMS + (2 * SMP * CXP) + .004 * .5 IF US = 1 THEN SUM = 0 PRINT PRINT " CHASSIS MASS, KG ", MAS PRINT PRINT INPUT "INPUT COMMAND POSTS QUANTUTY ", NP MYP = .75 * .3 * (LF + RK) + NP PRINT PRINT "WEIGHT OF CONTROLS, KG ", MYP SLEEP 1 CLS PRINT " MASS II APPROXIMATION" PRINT PRINT IF PKK = 0 THEN PRINT " MASS OF WING, KG, = "; CINT(MK2) IF PKK = 1 THEN PRINT " MASS OF WING WITH STRUTS, KG, = "; CINT(MK2) IF PKK = 2 THEN PRINT " MASS OF WING, KG, = "; CINT(MK2) PRINT " FUSELAGE MASS * KG, = "; CINT(MF2) PRINT " FUEL MASS KG, = "; MAT PRINT " POWER PLANT MASS, KG = "; SU PRINT " TAIL VFSS, KG = "; CINT(MO) PRINT " CHASSIS MASS,KG = "; CINT(MAS) PRINT " CONTROLS MASS, KG = "; CINT(MYP) IF NP = 1 THEN NPP = 80: PRINT " MASS OF PILOT KG, = "; 80 IF NP = 2 THEN NPP = 160: PRINT " MASS OF PILOTS KG, = "; 160 MS2 = MK2 + MF2 + MAT + SU + MO + MAS + MYP + NPP MPS = MK2 + MF2 + SU + MO + MAS + MYP PRINT IF GS1 < 350 THEN PRINT " * CANOPY = 3,CONTROL DEVICES = 3,SEAT = 2,ENGINE MOUNT = 2,FURNITURE = 1 kg; TOTAL ="; VA IF GS1 >= 350 THEN PRINT " * CANOPY = 4,CONTROL DEVICES = 4,SEAT = 4,ENGINE MOUNT = 2,FURNITURE = 1 kg; TOTAL ="; VA 6 PRINT PRINT PRINT " MASS I APPROXIMATION EQUALS KG, = "; GS1 PRINT " MASS II APPROXIMATION EQUALS KG, = "; INT(MS2) PRINT " THE DRY WEIGHT OF THE GLIDER (PLANER) DESIGNED KG, = "; INT(MPS) PRINT PRINT INPUT " ENTER MASS III APPROXIMATION, KG = ", GS PRINT INPUT " REPEAT MASS CALCULATION ? y -1; N -0 ", RET IF RET = 1 THEN GOTO 1 SLEEP 1: CLS SCREEN 2 LOCATE 12, 15: INPUT " WILL MASS ALIGNMENT BE UPDATED ? Y - 1 , N - 0", CE IF CE = 1 THEN GOTO 7 IF CE = 0 THEN GOTO 9 7 REM MASS ALIGNMENT CLS SCREEN 1 COLOR 1 VIEW (10, 10)-(300, 180), , 1 LOCATE 10, 10: PRINT " DETERMINATION OF THE CENTRE" LOCATE 15, 10: PRINT " OF GRAVITY OF THE AIRCRAFT " SLEEP 2 CLS 8 SCREEN 12: COLOR 3 LOCATE 1, 32: PRINT "MASS ALIGNMENT SHEET" FOR I = 2 TO 79 LOCATE 2, I: PRINT CHR$(45) NEXT I FOR I = 1 TO 80 LOCATE 4, I: PRINT CHR$(45) NEXT I FOR I = 1 TO 80 LOCATE 23, I: PRINT CHR$(95) NEXT I FOR I = 3 TO 23 LOCATE I, 1: PRINT CHR$(179) NEXT I FOR I = 3 TO 23 LOCATE I, 80: PRINT CHR$(179) NEXT I FOR I = 3 TO 23 LOCATE I, 6: PRINT CHR$(179) NEXT I FOR I = 3 TO 23 LOCATE I, 35: PRINT CHR$(179) NEXT I FOR I = 3 TO 23 LOCATE I, 50: PRINT CHR$(179) NEXT I FOR I = 3 TO 23 LOCATE I, 65: PRINT CHR$(179) NEXT I LOCATE 3, 2: PRINT " N " LOCATE 3, 15: PRINT " UNIT " LOCATE 3, 37: PRINT " MASS, KG " LOCATE 3, 52: PRINT " LEVER, M " LOCATE 3, 67: PRINT " TORQUR, KG * M " FOR N = 1 TO 18 LOCATE N + 4, 2: PRINT N NEXT N LOCATE 5, 8: PRINT "PROPELLER + PROP COVER": LOCATE 5, 37: PRINT "(4-5)": LOCATE 5, 45: INPUT "", MV: LOCATE 5, 57: INPUT "", PV: LOCATE 5, 71: PRINT MV * PV LOCATE 6, 8: PRINT "ENGINE + REDUCTOR": LOCATE 6, 45: INPUT "", MD: LOCATE 6, 57: INPUT "", PD: LOCATE 6, 71: PRINT PD * MD LOCATE 7, 8: PRINT "ENGINE MOUNT + ENGINE COVERS": LOCATE 7, 37: PRINT "(2+3)": LOCATE 7, 45: INPUT "", MM: LOCATE 7, 57: INPUT "", PM: LOCATE 7, 71: PRINT MM * PM LOCATE 8, 8: PRINT "PEDALS": LOCATE 8, 37: PRINT "(2)": LOCATE 8, 45: INPUT "", MPP: LOCATE 8, 57: INPUT "", PPP: LOCATE 8, 71: PRINT MPP * PPP LOCATE 9, 8: PRINT "FRONT (REAR) CHASSIS STRUT": LOCATE 9, 37: PRINT "(5-6)": LOCATE 9, 45: INPUT "", MS: LOCATE 9, 57: INPUT "", PS: LOCATE 9, 71: PRINT MS * PS LOCATE 10, 8: PRINT "TANK + FUEL": LOCATE 10, 45: INPUT "", MT: LOCATE 10, 57: INPUT "", PT: LOCATE 10, 71: PRINT MT * PT LOCATE 11, 8: PRINT "CONTROL DEVICES": LOCATE 11, 37: PRINT "(3.5)": LOCATE 11, 45: INPUT "", MMP: LOCATE 11, 57: INPUT "", PMP: LOCATE 11, 71: PRINT MMP * PMP LOCATE 12, 8: PRINT "CONTROL STICK": LOCATE 12, 37: PRINT "(3)": LOCATE 12, 45: INPUT "", MU: LOCATE 12, 57: INPUT "", PU: LOCATE 12, 71: PRINT PU * MU LOCATE 13, 8: PRINT "CANOPY": LOCATE 13, 37: PRINT "(3-4)": LOCATE 13, 45: INPUT "", MF: LOCATE 13, 57: INPUT "", PF: LOCATE 13, 71: PRINT MF * PF LOCATE 14, 8: PRINT "FUSELAGE + SEAT(S)": LOCATE 14, 45: INPUT "", MFO: LOCATE 14, 57: INPUT "", PFO: LOCATE 14, 71: PRINT MFO * PFO LOCATE 15, 8: PRINT "WING WITH AILERONS": LOCATE 15, 45: INPUT "", MAK: LOCATE 15, 57: INPUT "", PAK: LOCATE 15, 71: PRINT PAK * MAK LOCATE 16, 8: PRINT "PILOT(S)": LOCATE 16, 37: PRINT "(kg 80)": LOCATE 16, 45: INPUT "", ML: LOCATE 16, 57: INPUT "", MPL: LOCATE 16, 71: PRINT ML * MPL LOCATE 17, 8: PRINT "MAIN CHASSIS": LOCATE 17, 45: INPUT "", MOS: LOCATE 17, 57: INPUT "", PPS: LOCATE 17, 71: PRINT PPS * MOS LOCATE 18, 8: PRINT "THE FAIRING (GARGROT)": LOCATE 18, 37: PRINT "(2-3)": LOCATE 18, 45: INPUT "", MG: LOCATE 18, 57: INPUT "", PG: LOCATE 18, 71: PRINT MG * PG LOCATE 19, 8: PRINT "STABILISER": LOCATE 19, 45: INPUT "", MSS: LOCATE 19, 57: INPUT "", PSS: LOCATE 19, 71: PRINT MSS * PSS LOCATE 20, 8: PRINT "THE ELEVATOR": LOCATE 20, 45: INPUT "", MRV: LOCATE 20, 57: INPUT "", PRV: LOCATE 20, 71: PRINT MRV * PRV LOCATE 21, 8: PRINT "KEEL": LOCATE 21, 45: INPUT "", MKI: LOCATE 21, 57: INPUT "", PKI: LOCATE 21, 71: PRINT MKI * PKI LOCATE 22, 8: PRINT "RUDDER": LOCATE 22, 45: INPUT "", MRN: LOCATE 22, 57: INPUT "", PRN: LOCATE 22, 71: PRINT PRN * MRN XAT = MV * PV + PD * MD + MM * PM + MPP * PPP + MS * PS + MT * PT + MMP * PMP + PU * MU + MF * PF + MFO * PFO + PAK * MAK + ML * MPL + PPS * MOS + MG * PG + MSS * PSS + MRV * PRV + MKI * PKI + PRN * MRN ME = MV + MD + MM + MPP + MS + MT + MMP + MU + MF + MFO + MAK + ML + MOS + MG + MSS + MRV + MKI + MRN XT = XAT / ME LOCATE 25, 2: INPUT "ENTER THE COORDINATE OF THE SOCK WING, M ", XN XOK = XT - XN XOT = XOK / XK / 100 * 10000 SLEEP 1: CLS SCREEN 1 COLOR 1 VIEW (10, 10)-(300, 180), , 1 LOCATE 9, 11: PRINT "MASS CENTER" LOCATE 10, 16: PRINT "COORDINATES" LOCATE 12, 13: PRINT "Xt ="; XT LOCATE 14, 13: PRINT "Xt%="; XOT LOCATE 16, 13: PRINT "Gcalculated ="; ME SLEEP 5 LOCATE 22, 3: INPUT "REPEAT CALCULATION ? Y -1 , N -0", YY IF YY = 1 THEN GOTO 8 IF YY = 0 THEN GOTO 9 9 CLS IF NN = 0 THEN GOTO 12 SCREEN 1: VIEW (10, 10)-(300, 180), , 4 COLOR 1 LOCATE 6, 15: PRINT "DETERMINATION" LOCATE 9, 15: PRINT "OF THE OPTIMAL" LOCATE 12, 17: PRINT "LOADS" LOCATE 15, 19: PRINT "ON THE" LOCATE 18, 18: PRINT "WING" SLEEP 2 CLS PSR = 2 * ND: FK = .1 REM THE GRAPH DIM T(70) DIM R(70) DIM I(70) DIM U(670) SCREEN 2 LINE (40, 4)-(40, 164) FOR N = 4 TO 164 STEP 16 ' VERTICAL ' FOR Q = 40 TO 45 PRESET (Q, N), 1 NEXT Q NEXT N FOR N = 1 TO 10 LOCATE 1 + N * 2, 1: PRINT 160 - 16 * N NEXT N LINE (40, 164)-(560, 164) FOR N = 80 TO 560 STEP 40 LOCATE 22, N / 8 - 1: PRINT N / 10 FOR Q = 161 TO 163 PRESET (N, Q), 1 NEXT Q ' HORIZONTAL ' NEXT N LOCATE 1, 11: PRINT " CHOOSING OF THE OPTIMAL WING LOADING , DEPENDING ON THE WEIGHT OF THE WING " LOCATE 1, 1: PRINT " G wing, KG" LOCATE 2, 1: PRINT " L takeoff, M" LOCATE 21, 75: PRINT "G/S" LOCATE 22, 74: PRINT "kg/m" LOCATE 23, 30: INPUT "Enter Cy takeoff = ", CYP DGS = 560 / 56 FOR N = 5 TO 9 ' elongation ' FOR Q = 16 TO 56 STEP 4 ' for G/S' S1 = GS / Q R(Q) = CINT(.0001 * KKK * GS * NR * (N * 4 * SQR(S1) * SQR(15))) IF PKK = 1 OR PKK = 2 THEN R(Q) = R(Q) * .7 R(12) = R(Q) T(Q) = Q T(12) = 16 IF R(Q) >= 124 THEN GOTO 10 LINE (DGS * T(Q - 4), 164 - R(Q - 4))-(DGS * T(Q), 164 - R(Q)) 10 I(Q) = CINT(GS / (S1 * CYP * 9.81 * .125 * (.91 * PSR / GS - FK))) I(12) = I(Q) IF I(Q) >= 136 THEN GOTO 11 LINE (DGS * T(Q - 4), 164 - I(Q - 4))-(DGS * T(Q), 164 - I(Q)) 11 NEXT Q IF I(16) >= 136 THEN GOTO 121 LOCATE INT((164 - I(16)) / 8) + 1, INT(DGS * T(16) / 8) - 6: PRINT "L takeoff" 121 NEXT N LOCATE 2, 32: PRINT " AND TAKEOFF RUNNING LENTH" LOCATE 3, 24: PRINT "G/S ="; INT(GS / SK) LAM = RK ^ 2 / SK IF FAF = 4 THEN LAM = (RK / .83) ^ 2 / SK LOCATE 3, 67: PRINT "ELONGATION="; INT(LAM * 10) / 10 LOCATE 3, 49: PRINT "Cy takeoff ="; CYP LOCATE 3, 11: PRINT "G ="; GS IF NN = 11 THEN GOTO 61 LOCATE 3, 37: PRINT FI$ GOTO 62 61 LOCATE 3, 37: PRINT ND: LOCATE 3, 41: PRINT "HP" 62 IF R(56) >= 136 THEN GOTO 45 LOCATE INT((164 - R(56)) / 8), INT(DGS * T(56) / 8) - 3: PRINT "ELONGATION" LOCATE INT((164 - R(56)) / 8) + 1, INT(DGS * T(56) / 8) + 2: PRINT "9" LOCATE INT((164 - R(56)) / 8) + 2, INT(DGS * T(56) / 8) + 2: PRINT "8" LOCATE INT((164 - R(56)) / 8) + 3, INT(DGS * T(56) / 8) + 2: PRINT "7" LOCATE INT((164 - R(56)) / 8) + 4, INT(DGS * T(56) / 8) + 2: PRINT "6" LOCATE INT((164 - R(56)) / 8) + 5, INT(DGS * T(56) / 8) + 2: PRINT "5" 45 SLEEP 2 LOCATE 23, 6: INPUT "TO COMPLETE THE WORK -0; New Cy takeoff -1; change wing area -2; continue -3 ", ZAV IF ZAV = 0 THEN GOTO 44 IF ZAV = 1 THEN GOTO 9 IF ZAV = 3 THEN GOTO 12 IF ZAV = 2 THEN SE = SS + 1: GOTO 200 12 CLS RO = .125: PI = 3.141592 SCREEN 1: COLOR 1: VIEW (10, 10)-(300, 180), , 1 LOCATE 10, 9: PRINT " The PROGRAM determine" LOCATE 12, 10: PRINT " the LOADS ON the" LOCATE 14, 17: PRINT " STRAIGHT WING " SLEEP 1: CLS LOCATE 3, 10: PRINT " BOUNDARY CONDITIONS:" LOCATE 7, 3: PRINT "1. WING IS RECTANGULAR " LOCATE 9, 3: PRINT "2. WING IS NOT TWISTED " LOCATE 11, 3: PRINT "3. THE ELONGATION OF THE WING 5 .8 AND SIG <= .9 THEN T1(N) = SIG / 2 - .05: IF SIG > .9 AND SIG <= 1 THEN T1(N) = SIG / 2 + .1 TT(N) = T1(N) * HL LOCATE 25, 1: PRINT "0>9" LOCATE 25, (N + 1) * 7: PRINT (INT(TT(N) * 100)) / 100 LOCATE 25, 77: PRINT "CM" NEXT N 14 SLEEP 4: LOCATE 28, 1: INPUT " WILL ENTER OTHER DATA ? YES - 1 ; NO - 0", ZZ IF ZZ = 1 THEN RESTORE: GOTO 1 IF ZZ = 0 THEN GOTO 17 17 IF PKK = 1 OR PKK = 2 THEN GOTO 18 IF PKK = 0 THEN GOTO 22 18 CLS: SLEEP 1 REM SUBROUTINE BUILD AXES SCREEN 2 PRINT "M, KG* M " LOCATE 1, 9: PRINT "R,kg " LOCATE 1, 37: PRINT " SECTION 10 CORRESPONDS TO THE END OF THE WING" LOCATE 2, 37: PRINT " M - BENDING MOMENT" LOCATE 3, 37: PRINT " R - REACTION SUPPORTS (BRACE, AND THE HINGE)" LINE (56, 0)-(56, 180) ' VERTICAL' FOR N = 0 TO 186 STEP 12 FOR Q = 57 TO 65 PRESET (Q, N), 1 NEXT Q NEXT N REM DIGITIZATION DD = D(0) / 5 FOR N = 0 TO 5 LOCATE 2 + N * 3, 1: PRINT CINT(D(0) - DD * N) NEXT N LINE (56, 132)-(560, 132) FOR N = 56 TO 616 STEP 56 LOCATE 18, N / 8: PRINT (N / 56) - 1 ' HORIZONTAL ' FOR Q = 128 TO 131 PRESET (N, Q), 1 NEXT Q NEXT N REM PLOTTING SCREEN 2 KGP = D(0) / 120 FOR N = 10 TO 0 STEP -1 H(11) = 0 H(N) = INT(D(N) / KGP) PRESET (56 + 56 * N, 132 - H(N)), 1 ' BY DOTS' LINE (56 + (56 * (N + 1)), 132 - H(N + 1))-(56 + (56 * N), 132 - H(N)) NEXT N LOCATE 17, 79: PRINT " L" IF PKK = 0 THEN GOTO 22 19 IF PKK = 1 THEN LOCATE 23, 12: INPUT " ENTER THE POINT OF ATTACHMENT OF THE BRACE FROM THE END OF THE WING , M", OK IF PKK = 2 THEN LOCATE 23, 12: INPUT " ENTER THE POINT OF ATTACHMENT OF THE STREAMERS FROM THE END OF THE WING , M", OK 20 PK = LK - OK LPOD = SQR(HF ^ 2 + PK ^ 2) KOP = NPO * 2 SUL = LPOD * KOP IF PKK = 2 THEN CXPP = SUL * .0008 ' tape thickness 3 mm ' IF SPO = 2 AND GS1 < 300 THEN CXPP = SUL * .0016 ' d=30,Cx*S 1M=0.0016 ' IF SPO = 2 AND GS1 >= 300 THEN CXPP = SUL * .0022 ' d=40,Cx*S 1M=0.0022 ' IF SPO = 1 AND GS1 < 300 THEN CXPP = SUL * .0068 ' a=25,a/b=0.5 Cx=0.2725 ' IF SPO = 1 AND GS1 >= 300 THEN CXPP = SUL * .01 ' a=36,a/b=0.5 Cx=0.2725 ' IF SPO = 0 AND GS1 < 300 THEN CXPP = SUL * .035 ' d=35,Cx*S 1M=1 ' IF SPO = 0 AND GS1 >= 300 THEN CXPP = SUL * .045 ' d=45,Cx*S 1M=1 ' DCX1 = .0013 21 XD = D(0) / B(0) ' CENTER OF PRESSURE (?)' RP = B(0) * XD / PK R2 = B(0) - RP DX = LK / 560 LOCATE 10, 40: PRINT "R podk = "; INT(RP) LOCATE 14, 12: PRINT "R0 = "; INT(R2) FOR N = 616 TO 56 STEP -1 X = LK - ((N - 56) * DX) REM IML - THE INTERPOLATION POLYNOMIAL OF LAGRANGE IML = ((X - L(6)) * (X - L(4)) * (X - LK)) / ((L(8) - L(6)) * (L(8) - L(4)) * (L(8) - LK)) * D(8) + ((X - L(8)) * (X - L(4)) * (X - LK)) / ((L(6) - L(8)) * (L(6) - L(4)) * (L(6) - LK)) * D(6) + ((X - L(8)) * (X - L(6)) * (X - LK)) / ((L(4) - L(8)) * (L(4) - L(6)) * (L(4) - LK)) * D(4) + ((X - L(8)) * (X - L(6)) * (X - L(4))) / ((LK - L(8)) * (LK - L(6)) * (LK - L(4))) * D(0) KO = (INT(IML / KGP)) IF X <= OK THEN PRESET (N, 132 - KO), 1 IF X <= OK THEN LOCATE 13, 48: PRINT INT(IML) PR = (INT((IML - (RP * ABS(X - OK))) / KGP)) U(N) = INT((IML - (RP * ABS(X - OK)))) U(617) = U(616) - 50 IF X > OK THEN PRESET (N, 132 - PR), 1 IF X > OK AND U(N) < U(N + 1) THEN LOCATE 20, 24: PRINT INT((IML - (RP * ABS(X - OK)))) NEXT N LOCATE 23, 12: INPUT " TO ENTER A DIFFERENT ATTACHMENT POINT ? YES -1 , NO -0 ", TK IF TK = 1 THEN GOTO 19 IF TK = 0 THEN GOTO 22 22 SLEEP 1: CLS SCREEN 1: COLOR 1: VIEW (10, 10)-(300, 180), , 1 LOCATE 9, 11: PRINT " AERODYNAMICAL " LOCATE 12, 16: PRINT " CALCULATING " LOCATE 15, 15: PRINT " OF AIRPLANE " SLEEP 2: CLS: SCREEN 12: COLOR 3 REM WING REM ' Re FOR SPEED 120-130 KM/H = 2.39 - 3.8, WE NAKE Re = 3 ' CXPPO = CXPP / SK IF FAF = 1 OR FAF = 2 OR FAF = 3 OR FAF = 5 THEN KCXP = CXPK * (1 - KAB * (SPF / SK)) + DCX1 + CXPPO IF FAF = 4 THEN KCXP = 1.5 * CXPK * (1 - KAB * (SPF / SK)) + DCX1 + CXPPO PRINT PRINT REM FUSELAGE LAF = INT(.88 * LF / SQR(SM)) IF LAF = 3 THEN NUF = 1.5 IF LAF = 4 THEN NUF = 1.3 IF LAF = 5 THEN NUF = 1.233 IF LAF = 6 THEN NUF = 1.166 IF LAF = 7 THEN NUF = 1.133 IF LAF = 8 THEN NUF = 1.111 IF LAF = 9 THEN NUF = 1.1 IF LAF = 10 THEN NUF = .8 REF = INT(35 * LF / 14.8) IF REF = 6 THEN CFR = .00325 IF REF = 7 THEN CFR = .00316 IF REF = 8 THEN CFR = .00308 IF REF = 9 THEN CFR = .003 IF REF = 10 THEN CFR = .00292 IF REF = 11 THEN CFR = .00288 IF REF = 12 THEN CFR = .00284 IF REF = 13 THEN CFR = .0028 IF REF = 14 THEN CFR = .00275 IF REF = 15 THEN CFR = .0027 IF REF = 16 THEN CFR = .00267 IF REF = 17 THEN CFR = .00262 IF REF = 18 THEN CFR = .00258 IF RD = 2 AND KLAM = 1 THEN CFR = CFR - .0005 ' FOR LAMINARY FUSELAGE ' SOM = 2.85 * LF * SQR(SM) 24 IF KOF = 1 THEN COF = .65 IF KOF = 2 THEN COF = .1 IF KOF = 3 THEN COF = .04 IF KOF = 4 THEN COF = .012 IF KOF = 5 THEN COF = .01 IF KOF = 6 THEN COF = .005 IF KOF = 7 THEN COF = .004 REM ' WE TAKE Sfon/Smid = 0.333 ' CXPF = CFR * NUF * SOM / SM IF RD = 1 AND DVZ = 1 THEN DCXF = .025 IF RD = 1 AND DVZ = 0 THEN DCXF = .04 IF RD = 2 AND DVZ = 1 THEN DCXF = .035 IF RD = 2 AND DVZ = 0 THEN DCXF = .06 IF RD = 2 AND DVZ = 2 THEN DCXF = 0 CXF = CXPF + DCXF + COF * (SM * .333 / SM) + .0103 CLS REM HORIZONTAL TAIL IF PGO = 0 THEN CXPO = 1.85 * .00425 * 1.3: CXG0 = CXPO * (1 - .9 * .03) + .003 IF PGO = 1 THEN CXPO = 1.85 * .00425 * 1.3: CXGO = CXPO * (1 - .9 * .03) + .00572 ' 2 for 0.7 Cx 1M = .004 ' IF PGO = 2 THEN CXPO = 1.85 * .00425 * 1.3: CXGO = CXPO * (1 - .9 * .03) + .00493 ' 4 for 0.7 Cx 1M = .00176 ' SOG = SGO / SK REM 'OTNOMASHCHINA 6-9% Nu = 1.3, Re = 1/2 WINGS OF THE WING, COEF. INTERFERENCES CAV = .9, SPF / S = .03 ' REM VERTICAL TAIL SOV = SVO / SK REM ' Spf/S = .01 , KAB = .85 CXVO = CXPO * (1 - .85 * .01) + .003 SXDV = 0 ' HONDOLLS ' CXO = 1.1 * (KCXP + CXGO * SOG + CXVO * SOV + CXF * (SM / SK) + SUM * ((SMS + SMP) / SK) + SXDV) COX = CXO / 100 / 1.1 REM CALCULATING COEFF A L = (INT(LAM * 10)) / 10 LL = L * .01 - .0025 IF FAF = 1 THEN SZF = 0 IF FAF = 2 OR FAF = 3 OR FAF = 5 THEN SZF = SPF / SK IF FAF = 4 THEN SZF = SPF / SK / 2 LEF = .9 * L / (1 + SZF) A = (1 + LL) / (PI * LEF): CLS PRINT " EQUATION OF THE AIRPLANE POLAR: CX = "; CXO; " + "; A; " * Cy2" LOCATE 1, 70: PRINT FG$ FOR I = 2 TO 79 LOCATE 2, I: PRINT CHR$(45): NEXT I FOR I = 4 TO 22 STEP 2 ' HORIZONTAL ' FOR T = 1 TO 80 LOCATE I, T: PRINT CHR$(45) NEXT T: NEXT I FOR I = 2 TO 22 LOCATE I, 1: PRINT CHR$(179): NEXT I FOR I = 3 TO 21 LOCATE I, 6: PRINT CHR$(179): NEXT I FOR I = 3 TO 21 FOR O = 15 TO 60 STEP 15 ' VERTICAL ' LOCATE I, O: PRINT CHR$(179) NEXT O: NEXT I FOR I = 3 TO 21 LOCATE I, 70: PRINT CHR$(179): NEXT I FOR I = 2 TO 22 LOCATE I, 80: PRINT CHR$(179): NEXT I LOCATE 3, 2: PRINT "ANGLE" LOCATE 3, 10: PRINT "Cy" LOCATE 3, 20: PRINT "Cx of airplane" LOCATE 3, 34: PRINT "K = Cy/Cx" LOCATE 3, 48: PRINT "HORIZONTAL SPEED, KM/H" LOCATE 3, 72: PRINT "N, HP" LOCATE 3, 62: PRINT "P, KG." DATA 16,14,12,10,8,6,4,2,0 FOR I = 5 TO 21 STEP 2 READ K LOCATE I, 2: PRINT K NEXT I X(3) = CXO + A * Y(3) * Y(3) + DDX FOR N = 21 TO 5 STEP -2 LOCATE 26 - N, 8: PRINT Y(N) CYO = Y(N) / CYM IF CYO <= .4 THEN DDX = 0 IF CYO > .4 AND CYO <= .5 THEN DDX = .0005 IF CYO > .5 AND CYO <= .6 THEN DDX = .001 IF CYO > .6 AND CYO <= .7 THEN DDX = .0025 IF CYO > .7 AND CYO <= .8 THEN DDX = .005 IF CYO > .8 AND CYO <= .85 THEN DDX = .007 IF CYO > .85 AND CYO <= .9 THEN DDX = .01 IF CYO > .9 AND CYO <= .95 THEN DDX = .015 IF CYO > .95 AND CYO <= .98 THEN DDX = .02 IF CYO > .98 THEN DDX = .03 X(N) = CXO + A * Y(N) * Y(N) + DDX LOCATE 26 - N, 16: PRINT X(N) IF N = 5 AND Y(5) = 0 THEN LOCATE 26 - N, 37: PRINT "0": LOCATE 26 - N, 53: PRINT "-": LOCATE 26 - N, 65: PRINT "-": LOCATE 26 - N, 75: PRINT "-": V(5) = V(7): P(5) = P(7): N(5) = N(7): GOTO 25 KA = (INT(Y(N) / X(N) * 100)) / 100 LOCATE 26 - N, 35: PRINT KA V(N) = (INT(SQR(ABS((2 * GS) / (Y(N) * .125 * SK))) * 100)) / 100 LOCATE 26 - N, 49: PRINT V(N) * 3.6 P(N) = (INT(ABS(GS / KA) * 100)) / 100 LOCATE 26 - N, 62: PRINT P(N) N(N) = (INT(ABS(P(N) * V(N) / 75) * 100)) / 100 LOCATE 26 - N, 72: PRINT N(N) 25 NEXT N LOCATE 23, 2: PRINT " WING % ="; CINT(KCXP / COX) LOCATE 23, 23: PRINT " FUSELAGE % ="; CINT(CXF * (SM / SK) / COX) LOCATE 23, 45: PRINT " TAIL % ="; CINT((CXVO * SOV + CXGO * SOG) / COX) LOCATE 23, 67: PRINT " CHASSIS % ="; CINT(SUM * ((SMS + SMP) / SK) / COX) SLEEP 7 LOCATE 23, 1: INPUT " WILL SEE GRAPH? Y -1 , N -0 ", GH IF GH = 1 THEN GOTO 27 IF GH = 0 THEN GOTO 29 27 SCREEN 2 PRINT " Cy" LOCATE 1, 35: PRINT " POLAR OF THE PLANE " LOCATE 2, 25: PRINT " Cx ="; CXO; "+"; A; "* Cy2" LINE (40, 176)-(630, 176) ' HORIZONTAL ' FOR N = 40 TO 560 STEP 65 KDX = .26 / 520 ' STEP ? ' LOCATE 21, N / 8 - 2: PRINT INT(((N - 40) * KDX) * 100) / 100 ' DIGITIZATION ? ' FOR Q = 173 TO 176 PRESET (N, Q), 1 NEXT Q NEXT N LINE (40, 0)-(40, 176) ' VERTICAL ' FOR N = 0 TO 176 STEP 16 FOR Q = 40 TO 49 PRESET (Q, N), 1 NEXT Q NEXT N DY = CYM / 11 ' DIGITIZATION ' FOR N = 1 TO 10 LOCATE 1 + N * 2, 1: PRINT INT((CYM - (INT((DY * N) * 100)) / 100) * 100) / 100 NEXT N LOCATE 21, 77: PRINT "CXo" LOCATE 21, 6: PRINT "0 " DATA 0,2,4,6,8,10,12,14,16 KDY = 1.76 / 176 ' STEP ? ' Z(3) = INT(X(3) / KDX) FOR N = 5 TO 21 STEP 2 Z(N) = INT(X(N) / KDX) ' POINTS ON THE AXIS ? ' J(N) = (Y(N) / KDY) ' POINTS ON THE AXIS ? ' J(3) = J(N) READ S IF X(N) > .26 THEN GOTO 28 IF 176 - J(N) < 24 THEN GOTO 28 LOCATE INT((176 - J(N)) / 8), 4 + INT(Z(N) / 8): PRINT S PRESET (40 + INT((X(N) / KDX)), 176 - (Y(N) / KDY) - 2), 1 LINE (40 + Z(N - 2), 176 - J(N - 2))-(40 + Z(N), 176 - J(N)) 28 NEXT N LOCATE 13, 53: PRINT FG$ SLEEP: CLS INPUT "", EEEE 29 IF NN = 0 THEN GOTO 44 CLS: SCREEN 1: COLOR 1: VIEW (10, 10)-(300, 180), , 1 LOCATE 9, 14: PRINT " DEFINITION AVAILABLE THRUST AND POWER" LOCATE 11, 14: PRINT " OF REQUIRED AND" LOCATE 13, 13: PRINT " AVAILABLE " LOCATE 15, 12: PRINT " THRUST AND POWER" SLEEP 2: CLS SCREEN 12: COLOR 3 PRINT " THE AVAILABLE POWER AND PULL TWO-BLADE PROPELLER ENGLISH SERIES (RAF-6)" FOR I = 2 TO 79 LOCATE 2, I: PRINT CHR$(45): NEXT I FOR I = 2 TO 79 LOCATE 4, I: PRINT CHR$(45): NEXT I FOR I = 4 TO 22 STEP 2 FOR T = 1 TO 25 LOCATE I, T: PRINT CHR$(45) NEXT T: NEXT I FOR I = 4 TO 22 STEP 2 FOR T = 41 TO 80 LOCATE I, T: PRINT CHR$(45) NEXT T: NEXT I ' HORIZONTAL ' FOR I = 2 TO 79 LOCATE 22, I: PRINT CHR$(45): NEXT I FOR I = 2 TO 22 LOCATE I, 1: PRINT CHR$(179): NEXT I FOR I = 3 TO 21 LOCATE I, 14: PRINT CHR$(179): NEXT I FOR I = 3 TO 21 LOCATE I, 25: PRINT CHR$(179): NEXT I FOR I = 3 TO 21 LOCATE I, 41: PRINT CHR$(179): NEXT I FOR I = 3 TO 21 LOCATE I, 51: PRINT CHR$(179): NEXT I FOR I = 3 TO 21 LOCATE I, 65: PRINT CHR$(179): NEXT I FOR I = 2 TO 22 LOCATE I, 80: PRINT CHR$(179): NEXT I ' VERTICAL ' LOCATE 3, 3: PRINT "Vhorizont fl, km/h" LOCATE 3, 17: PRINT "STEP" LOCATE 3, 27: PRINT "coeff of power" LOCATE 3, 44: PRINT "KPD" LOCATE 3, 67: PRINT "Na, HP" LOCATE 3, 54: PRINT "Pa. KG" LOCATE 23, 1: INPUT " eNTER PROD DIAMETER , M ", DV IF DV <= 1.2 THEN BET = 75 * ND / (.125 * NOS ^ 3 * DV ^ 5) IF DV > 1.2 THEN BET = 75 * ND / (.125 * NORS ^ 3 * DV ^ 5) FOR N = 21 TO 5 STEP -2 IF N = 5 AND Y(5) = 0 THEN LOCATE 26 - N, 7: PRINT "-": LOCATE 26 - N, 19: PRINT "-" IF N = 5 AND Y(5) = 0 THEN LOCATE 26 - N, 46: PRINT "-": LOCATE 26 - N, 58: PRINT "-": LOCATE 26 - N, 72: PRINT "-": M(5) = M(7): O(5) = O(7): GOTO 30 LOCATE 26 - N, 4: PRINT V(N) * 3.6 IF DV <= 1.2 THEN LA = V(N) / NOS / DV IF DV > 1.2 THEN LA = V(N) / NORS / DV LOCATE 26 - N, 15: PRINT LA IF INT(BET * 1000) / 1000 >= .015 AND INT(BET * 1000) / 1000 <= .02 AND LA >= .2 AND LA <= .25 THEN KPD = .55 IF INT(BET * 1000) / 1000 >= .015 AND INT(BET * 1000) / 1000 <= .02 AND LA > .25 AND LA <= .3 THEN KPD = .57 IF INT(BET * 1000) / 1000 >= .015 AND INT(BET * 1000) / 1000 <= .02 AND LA > .3 AND LA <= .5 THEN KPD = .6 IF INT(BET * 1000) / 1000 >= .015 AND INT(BET * 1000) / 1000 <= .02 AND LA > .5 THEN KPD = .6 IF INT(BET * 1000) / 1000 > .02 AND INT(BET * 1000) / 1000 <= .025 AND LA > .2 AND LA <= .25 THEN KPD = .57 IF INT(BET * 1000) / 1000 > .02 AND INT(BET * 1000) / 1000 <= .025 AND LA > .25 AND LA <= .3 THEN KPD = .6 IF INT(BET * 1000) / 1000 > .02 AND INT(BET * 1000) / 1000 <= .025 AND LA > .3 AND LA <= .35 THEN KPD = .63 IF INT(BET * 1000) / 1000 > .02 AND INT(BET * 1000) / 1000 <= .025 AND LA > .35 AND LA <= .4 THEN KPD = .65 IF INT(BET * 1000) / 1000 > .02 AND INT(BET * 1000) / 1000 <= .025 AND LA > .4 THEN KPD = .67 IF INT(BET * 1000) / 1000 > .025 AND INT(BET * 1000) / 1000 <= .03 AND LA > .2 AND LA <= .25 THEN KPD = .55 IF INT(BET * 1000) / 1000 > .025 AND INT(BET * 1000) / 1000 <= .03 AND LA > .25 AND LA <= .3 THEN KPD = .6 IF INT(BET * 1000) / 1000 > .025 AND INT(BET * 1000) / 1000 <= .03 AND LA > .3 AND LA <= .35 THEN KPD = .63 IF INT(BET * 1000) / 1000 > .025 AND INT(BET * 1000) / 1000 <= .03 AND LA > .35 AND LA <= .4 THEN KPD = .65 IF INT(BET * 1000) / 1000 > .025 AND INT(BET * 1000) / 1000 <= .03 AND LA > .4 AND LA <= .5 THEN KPD = .7 IF INT(BET * 1000) / 1000 > .025 AND INT(BET * 1000) / 1000 <= .03 AND LA > .5 THEN KPD = .72 IF INT(BET * 1000) / 1000 > .03 AND INT(BET * 1000) / 1000 <= .035 AND LA > .2 AND LA <= .3 THEN KPD = .55 IF INT(BET * 1000) / 1000 > .03 AND INT(BET * 1000) / 1000 <= .035 AND LA > .3 AND LA <= .35 THEN KPD = .63 IF INT(BET * 1000) / 1000 > .03 AND INT(BET * 1000) / 1000 <= .035 AND LA > .35 AND LA <= .4 THEN KPD = .65 IF INT(BET * 1000) / 1000 > .03 AND INT(BET * 1000) / 1000 <= .035 AND LA > .4 AND LA <= .45 THEN KPD = .7 IF INT(BET * 1000) / 1000 > .03 AND INT(BET * 1000) / 1000 <= .035 AND LA > .45 AND LA <= .5 THEN KPD = .73 IF INT(BET * 1000) / 1000 > .03 AND INT(BET * 1000) / 1000 <= .035 AND LA > .5 THEN KPD = .75 IF INT(BET * 1000) / 1000 > .035 AND INT(BET * 1000) / 1000 <= .04 AND LA > .2 AND LA <= .3 THEN KPD = .55 IF INT(BET * 1000) / 1000 > .035 AND INT(BET * 1000) / 1000 <= .04 AND LA > .3 AND LA <= .35 THEN KPD = .6 IF INT(BET * 1000) / 1000 > .035 AND INT(BET * 1000) / 1000 <= .04 AND LA > .35 AND LA <= .4 THEN KPD = .65 IF INT(BET * 1000) / 1000 > .035 AND INT(BET * 1000) / 1000 <= .04 AND LA > .4 AND LA <= .5 THEN KPD = .72 IF INT(BET * 1000) / 1000 > .035 AND INT(BET * 1000) / 1000 <= .04 AND LA > .5 THEN KPD = .77 IF INT(BET * 1000) / 1000 > .04 AND INT(BET * 1000) / 1000 <= .05 AND LA > .2 AND LA <= .25 THEN KPD = .53 IF INT(BET * 1000) / 1000 > .04 AND INT(BET * 1000) / 1000 <= .05 AND LA > .25 AND LA <= .3 THEN KPD = .55 IF INT(BET * 1000) / 1000 > .04 AND INT(BET * 1000) / 1000 <= .05 AND LA > .3 AND LA <= .35 THEN KPD = .6 IF INT(BET * 1000) / 1000 > .04 AND INT(BET * 1000) / 1000 <= .05 AND LA > .35 AND LA <= .4 THEN KPD = .65 IF INT(BET * 1000) / 1000 > .04 AND INT(BET * 1000) / 1000 <= .05 AND LA > .4 AND LA <= .5 THEN KPD = .7 IF INT(BET * 1000) / 1000 > .04 AND INT(BET * 1000) / 1000 <= .05 AND LA > .5 AND LA <= .7 THEN KPD = .77 IF INT(BET * 1000) / 1000 > .04 AND INT(BET * 1000) / 1000 <= .05 AND LA > .7 THEN KPD = .8 IF INT(BET * 1000) / 1000 > .05 AND INT(BET * 1000) / 1000 <= .62 AND LA > .2 AND LA <= .25 THEN KPD = .53 IF INT(BET * 1000) / 1000 > .05 AND INT(BET * 1000) / 1000 <= .62 AND LA > .25 AND LA <= .3 THEN KPD = .55 IF INT(BET * 1000) / 1000 > .05 AND INT(BET * 1000) / 1000 <= .62 AND LA > .3 AND LA <= .35 THEN KPD = .57 IF INT(BET * 1000) / 1000 > .05 AND INT(BET * 1000) / 1000 <= .62 AND LA > .35 AND LA <= .4 THEN KPD = .6 IF INT(BET * 1000) / 1000 > .05 AND INT(BET * 1000) / 1000 <= .62 AND LA > .4 AND LA <= .45 THEN KPD = .65 IF INT(BET * 1000) / 1000 > .05 AND INT(BET * 1000) / 1000 <= .62 AND LA > .45 AND LA <= .5 THEN KPD = .69 IF INT(BET * 1000) / 1000 > .05 AND INT(BET * 1000) / 1000 <= .62 AND LA > .5 AND LA <= .6 THEN KPD = .75 IF INT(BET * 1000) / 1000 > .05 AND INT(BET * 1000) / 1000 <= .62 AND LA > .6 AND LA <= .7 THEN KPD = .77 IF INT(BET * 1000) / 1000 > .05 AND INT(BET * 1000) / 1000 <= .62 AND LA > .7 AND LA <= .8 THEN KPD = .8 IF INT(BET * 1000) / 1000 > .05 AND INT(BET * 1000) / 1000 <= .62 AND LA > .8 THEN KPD = .83 LOCATE 26 - N, 44: PRINT KPD 'KPD' M(N) = ND * KPD 'Np' LOCATE 26 - N, 69: PRINT M(N) O(N) = M(N) / V(N) * 75 'Pp' LOCATE 26 - N, 54: PRINT O(N) 30 NEXT N LOCATE 6, 27: PRINT BET LOCATE 10, 29: PRINT F$ IF NN = 11 THEN LOCATE 12, 29: PRINT ND: LOCATE 12, 34: PRINT "HP": GOTO 53 LOCATE 12, 30: PRINT FI$ 53 LOCATE 14, 29: PRINT "Dv =": LOCATE 14, 34: PRINT DV IF NN = 11 THEN GOTO 52 IF DV <= 1.2 THEN LOCATE 16, 29: PRINT N$ IF DV > 1.2 THEN LOCATE 16, 29: PRINT NR$ GOTO 60 52 IF DV <= 1.2 THEN LOCATE 16, 28: PRINT NOR: LOCATE 16, 34: PRINT "rpm" IF DV > 1.2 THEN LOCATE 16, 28: PRINT NOR: LOCATE 16, 34: PRINT "rpm" 60 LOCATE 23, 1: PRINT " ": SLEEP REM PLOTTING INPUT "", EV 32 SCREEN 2 LOCATE 1, 25: PRINT " REQUIRED AND AVAILABLE THRUST" LOCATE 1, 1: PRINT "Pr,kg Pa,kg" LINE (40, 4)-(40, 164) FOR N = 4 TO 164 STEP 16 ' VERTICAL ' FOR Q = 40 TO 44 PRESET (Q, N), 1 NEXT Q: NEXT N IF ND < 64 THEN GOTO 34 IF ND >= 64 AND ND <= 100 THEN GOTO 33 IF ND > 100 THEN GOTO 127 33 DYP = 240 / 160 FOR N = 1 TO 10 LOCATE 1 + N * 2, 1: PRINT INT(((240 - ((INT((16 * DYP * N) * 100)) / 100)) * 100) / 100) NEXT N GOTO 35 34 DYP = 160 / 160 '1 DOT - 1 KG THRUST' FOR N = 1 TO 10 LOCATE 1 + N * 2, 1: PRINT INT(((160 - ((INT((16 * DYP * N) * 100)) / 100)) * 100) / 100) NEXT N GOTO 35 127 DYP = 320 / 160 FOR N = 1 TO 10 LOCATE 1 + N * 2, 1: PRINT INT(((320 - ((INT((16 * DYP * N) * 100)) / 100)) * 100) / 100) NEXT N 35 LINE (40, 164)-(580, 164) FOR N = 40 TO 560 STEP 40 LOCATE 22, N / 8 + 4: PRINT N / 2 ' HORIZONTAL ' FOR Q = 160 TO 162 PRESET (N, Q), 1 NEXT Q: NEXT N LOCATE 22, 75: PRINT "V,KM/H" DXV = 2 ' IN 1 KM/H = 2 DOTS ' W(5) = INT(P(5) / DYP) S(5) = INT(O(5) / DYP) FOR N = 7 TO 21 STEP 2 W(N) = INT(P(N) / DYP) ' THRUST Pr ' S(N) = INT(O(N) / DYP) ' THRUST Pa ' IF Y(5) = 0 THEN P(5) = P(7): O(5) = O(7): V(5) = V(7) IF V(N) > 300 THEN GOTO 36 LINE (40 + INT((V(N - 2) * 3.6 * DXV)), 164 - W(N - 2))-(40 + INT((V(N) * 3.6 * DXV)), 164 - W(N)) LINE (40 + INT((V(N - 2) * 3.6 * DXV)), 164 - S(N - 2))-(40 + INT((V(N) * 3.6 * DXV)), 164 - S(N)) 36 NEXT N LOCATE INT((164 - W(21)) / 8) + 1, 5 + INT((V(21) * 3.6 * DXV) / 8): PRINT "Pr" IF S(21) >= 156 THEN GOTO 37 LOCATE INT((164 - S(21)) / 8) + 1, 5 + INT((V(21) * 3.6 * DXV) / 8): PRINT "Pa" 37 IF NN = 11 THEN LOCATE 2, 21: PRINT F$: LOCATE 2, 32: PRINT ND: LOCATE 2, 36: PRINT "HP": LOCATE 2, 53: PRINT "Dv ="; DV: GOTO 55 LOCATE 2, 21: PRINT F$: LOCATE 2, 32: PRINT FI$: LOCATE 2, 53: PRINT "Dv ="; DV 55 LOCATE 4, 30: PRINT "Vcr=1.2*Vnv=Dflight max" IF NN = 11 THEN GOTO 50 IF DV <= 1.2 THEN LOCATE 2, 42: PRINT N$ IF DV > 1.2 THEN LOCATE 2, 42: PRINT NR$ GOTO 51 50 IF DV <= 1.2 THEN LOCATE 2, 41: PRINT NOR: LOCATE 2, 47: PRINT "RPM" IF DV > 1.2 THEN LOCATE 2, 41: PRINT NOR: LOCATE 2, 47: PRINT "RPM" 51 SLEEP INPUT "", ZE VIEW (46, 1)-(600, 150), , 0 CLS 1 LOCATE 1, 23: PRINT "REQUIRED AND AVAILABLE CAPACITY" IF NN = 11 THEN LOCATE 2, 21: PRINT F$: LOCATE 2, 32: PRINT ND: LOCATE 2, 36: PRINT "HP": LOCATE 2, 53: PRINT "Dv ="; DV: GOTO 54 LOCATE 2, 21: PRINT F$: LOCATE 2, 32: PRINT FI$: LOCATE 2, 53: PRINT "Dv ="; DV 54 IF NN = 11 THEN GOTO 48 IF DV <= 1.2 THEN LOCATE 2, 42: PRINT N$ IF DV > 1.2 THEN LOCATE 2, 42: PRINT NR$ GOTO 49 48 IF DV <= 1.2 THEN LOCATE 2, 41: PRINT NOR: LOCATE 2, 47: PRINT "rpm" IF DV > 1.2 THEN LOCATE 2, 41: PRINT NOR: LOCATE 2, 47: PRINT "rpm" 49 LOCATE 1, 1: PRINT "Nr,hp. , Na,hp" LOCATE 4, 29: PRINT "Veco=Vmin horiz fl=T max fl" IF ND <= 80 THEN GOTO 128 IF ND > 80 THEN GOTO 129 128 DYPA = 80 / 160 ' 1 dot - 0.5 HP ' FOR N = 1 TO 10 LOCATE 1 + N * 2, 1: PRINT INT(((80 - ((INT((16 * DYPA * N) * 100)) / 100)) * 100) / 100) NEXT N GOTO 130 129 DYPA = 160 / 160 FOR N = 1 TO 10 LOCATE 1 + N * 2, 1: PRINT INT(((160 - ((INT((16 * DYPA * N) * 100)) / 100)) * 100) / 100) NEXT N 130 K(5) = INT(N(5) / DYPA) L(5) = INT(M(5) / DYPA) FOR N = 7 TO 21 STEP 2 K(N) = INT(N(N) / DYPA) ' Step Nr ' L(N) = INT(M(N) / DYPA) ' Step Na ' IF Y(5) = 0 THEN N(5) = N(7): M(5) = M(7) IF V(N) > 300 THEN GOTO 38 LINE (40 + INT((V(N - 2) * 3.6 * DXV)), 164 - K(N - 2))-(40 + INT((V(N) * 3.6 * DXV)), 164 - K(N)) LINE (40 + INT((V(N - 2) * 3.6 * DXV)), 164 - L(N - 2))-(40 + INT((V(N) * 3.6 * DXV)), 164 - L(N)) 38 NEXT N VY = INT(75 * ((M(17) - N(17)) / GS) * 100) / 100 LOCATE INT((164 - K(21)) / 8) + 1, 10 + INT((V(21) * 3.6 * DXV) / 8): PRINT "Nr" LOCATE INT((164 - L(21)) / 8), 10 + INT((V(21) * 3.6 * DXV) / 8): PRINT "Na" LOCATE INT((164 - K(21)) / 8) - 1, INT((V(21) * 3.6 * DXV) / 8) - 7: PRINT "Vy max ="; VY SLEEP CLS INPUT "", EEE SCREEN 1: COLOR 1: VIEW (10, 10)-(300, 180), , 1 LOCATE 10, 11: PRINT " TAKEOFF-LANDING " LOCATE 14, 14: PRINT "PERFOMANCE " 40 SLEEP 2: CLS SCREEN 12: COLOR 3 LOCATE 1, 30: PRINT " WING MECHANIZATION " PRINT INPUT " MECHANIZATION TYPE: NO MECHANISATION - 0 SIMPLE FLAP - 1 SLIT FLAP - 2 ", TM IF TM = 0 THEN DCYM = 0: R1 = 1: R2 = 1: R3 = 1: R4 = 1: GOTO 43 IF CO = 12 THEN R1 = 1.15 IF CO = 14 THEN R1 = 1.3 IF CO = 15 THEN R1 = 1.35 IF CO = 15.5 THEN R1 = 1.38 IF CO = 16 THEN R1 = 1.4 IF CO = 17 THEN R1 = 1.42 IF CO = 18 THEN R1 = 1.5 IF CO = 20 THEN R1 = 1.55 IF CO > 20 THEN R1 = 1.8 PRINT INPUT " flap span , m ", RZ ROT = INT(RZ / LK * 10) / 10 IF ROT >= .4 AND ROT <= .5 THEN R4 = .6 IF ROT >= .5 AND ROT <= .6 THEN R4 = .7 IF ROT >= .6 AND ROT <= .7 THEN R4 = .8 IF ROT >= .7 AND ROT <= .8 THEN R4 = .9 IF ROT >= .8 AND ROT <= .9 THEN R4 = .95 IF ROT >= .9 AND ROT <= 1 THEN R4 = 1 PRINT INPUT " FLAP CHORD , M ", XZO XZ = XZO / XK PRINT INPUT " FLAP TAKEOFF ANGLE, DEGREES ", UV PRINT INPUT " FLAP LANDING ANGLE, DEGREES ", UP PRINT PRINT IF TM = 1 THEN DCYM = .6: GOTO 41 IF TM = 2 THEN DCYM = .8: GOTO 42 41 IF UV = 15 THEN R2 = .3 IF UV = 17 THEN R2 = .4 IF UV = 18 THEN R2 = .42 IF UV = 20 THEN R2 = .45 IF UV = 25 THEN R2 = .55 IF UV = 30 THEN R2 = .62 IF UP = 20 THEN RR2 = .45 IF UP = 25 THEN RR2 = .55 IF UP = 30 THEN RR2 = .62 IF UP = 32 THEN RR2 = .7 IF UP = 35 THEN RR2 = .72 IF UP = 40 THEN RR2 = .83 IF UP = 45 THEN RR2 = .9 IF UP = 50 THEN RR2 = .97 IF UP = 60 THEN RR2 = 1.1 IF XZ >= .1 AND XZ <= .13 THEN R3 = .8 IF XZ > .13 AND XZ <= .15 THEN R3 = .9 IF XZ > .15 AND XZ <= .2 THEN R3 = .95 IF XZ > .2 AND XZ <= .25 THEN R3 = .98 IF XZ > .25 AND XZ <= .4 THEN R3 = 1 GOTO 43 42 IF UV = 15 THEN R2 = .6 IF UV = 17 THEN R2 = .7 IF UV = 18 THEN R2 = .72 IF UV = 20 THEN R2 = .75 IF UV = 25 THEN R2 = .85 IF UV = 30 THEN R2 = .9 IF UP = 20 THEN RR2 = .75 IF UP = 25 THEN RR2 = .85 IF UP = 30 THEN RR2 = .9 IF UP = 32 THEN RR2 = .95 IF UP = 35 THEN RR2 = .97 IF UP = 40 THEN RR2 = 1 IF UP = 45 THEN RR2 = .97 IF UP = 50 THEN RR2 = .82 IF UP = 60 THEN RR2 = .4 IF XZ >= .1 AND XZ <= .13 THEN R3 = .6 IF XZ > .13 AND XZ <= .15 THEN R3 = .7 IF XZ > .15 AND XZ <= .2 THEN R3 = .8 IF XZ > .2 AND XZ <= .25 THEN R3 = .9 IF XZ > .25 AND XZ <= .4 THEN R3 = 1 43 IF FF = 1 THEN CYM = .89 IF FF = 2 THEN CYM = .88 IF FF = 3 THEN CYM = 1.38 IF FF = 4 THEN CYM = 1.4 IF FF = 5 THEN CYM = .97 IF FF = 6 THEN CYM = 1.01 IF FF = 7 THEN CYM = 1.4 IF FF = 8 THEN CYM = 1.4 IF FF = 9 THEN CYM = 1 IF FF = 10 THEN CYM = 1.05 IF FF = 11 THEN CYM = 1 IF FF = 12 THEN CYM = 1.4 IF FF = 14 THEN CYM = 1.35 CMEX = CYM + DCYM * R1 * R2 * R3 * R4 CMEXP = CYM + DCYM * R1 * RR2 * R3 * R4 PRINT PRINT " TAKEOFF-LANDING CONDITIONS " PRINT INPUT " runway : DRY CONCTRETE -1; LIGHT WET CONCRETE -2; WET CONCRETE -3 SOLID GROUND -4; SOFT GROUND -5; THE SOIL VISCOUS -6 SAND-7; WET GRASS -8; DRY GRASS -9; ROLLED SNOW -10 ", FUT IF FUT = 1 THEN FTR = .03 IF FUT = 2 THEN FTR = .05 IF FUT = 3 THEN FTR = .07 IF FUT = 4 THEN FTR = .05 IF FUT = 5 THEN FTR = .1 IF FUT = 6 THEN FTR = .2 IF FUT = 7 THEN FTR = .25 IF FUT = 8 THEN FTR = .13 IF FUT = 9 THEN FTR = .09 IF FUT = 10 THEN FTR = .05 CLS PRINT " TAKEOFF-LANDING CHARACTERISTICS FOR " LOCATE 1, 58: PRINT FG$ PRINT PRINT PRINT " Cy takeoff =", INT(CMEX * 100) / 100: LOCATE 4, 31: PRINT "Takeoff angle = 12 degr" PRINT PRINT " THE STALL SPEED IN TAKEOFF CONFIGURATION , KM/H", INT(14.4 * SQR(INT(GS / SK / CMEX))) PRINT " THE SPEED OF SEPARATION IN TAKE-OFF CONFIGURATION , KM/H", INT(14.4 * SQR(INT(GS / SK / CMEX)) * 1.1) PRINT " THE MAXIMUM RATE OF CLIMB SPEED , KM/H ", INT(95 * SQR(SQR(SQR(SQR((GS / RK ^ 2)))))) PRINT " THE LENGTH OF THE takeoff RUN , M", INT(GS / (SK * CMEX * 9.81 * .125 * (.91 * (2 * ND) / GS - FTR))) PRINT PRINT CMEXPR = CMEXP PRINT " Cy landing =", INT(CMEXPR * 100) / 100: LOCATE 12, 29: PRINT "LANDING ANGLE = 12 degr" KNAB = .5 * (SQR(1 / A / CXO)) PRINT QQ = INT(14.4 * SQR(INT(GS / SK / CMEXPR))): QQQ = .125 * QQ ^ 2 \ 2 PRINT " THE BEGINNING SPEED OF LANDING , KM/H", INT(18.7 * SQR(INT(GS / SK / CMEXPR))) PRINT " THE SPEED OF LANDING , KM/H ", QQ PRINT " THE LENGTH OF THE BRAKING DISTANCE , M ", INT(.0045 * (14.4 * (SQR(INT(GS / SK / CMEXPR)))) ^ 2 / (.8 / KNAB + .25)) PRINT " THE LENGTH OF THE PATH FROM THE FRONT SUPPORT , M", INT(.0045 * (14.4 * (SQR(INT(GS / SK / CMEXPR)))) ^ 2 / (.8 / KNAB + FTR)) PRINT " THE LENGTH OF THE PATH FROM THE REAR SUPPORT , M", INT(.0045 * (14.4 * (SQR(INT(GS / SK / CMEXPR)))) ^ 2 / (.8 / KNAB + (.2 * FTR))) PRINT PRINT " EVOLUTION SPEED , KM/H ", INT(15.5 * SQR(GS / SK / CYM)) PRINT PRINT PRINT SLEEP 3 INPUT "UPDATE G/S OPTIMAL - 1 , UPDATE tf-PERFOMANCE - 2 , BEGIN - 3 , END - 0 TO CLARIFY THE PARAMETERS OF STABILITY OF PLANE - 4 ", UON IF UON = 1 THEN GOTO 9 IF UON = 2 THEN GOTO 40 IF UON = 3 THEN GOTO 1 IF UON = 0 THEN GOTO 117 IF UON = 4 THEN GOTO 100 44 CLS LOCATE 12, 17: INPUT " REPEAT CALCULATION -1 , END WORK -0 ", UON IF UON = 1 THEN SE = 1: GOTO 1 IF UON = 0 THEN GOTO 117 100 SCREEN 1: VIEW (10, 10)-(300, 180), , 4 COLOR 1 LOCATE 9, 9: PRINT "THE RATIO " LOCATE 13, 9: PRINT "OF THE LATERAL AND DIRECTIONAL STATIC" LOCATE 17, 9: PRINT "STABILITY OF THE AIRCRAFT" SLEEP 3: CLS 110 SCREEN 12: COLOR 3 PRINT " THE LATERAL AND DIRECTIONAL STATIC STABILITY OF THE AIRCRAFT" PRINT PRINT INPUT "ENTER the position of the CG RELATIVE to the FUSELAGE (Ct/Lf) , M ", XOF INPUT "ENTER THE HEIGHT OF THE canopy , M", HFO INPUT "ENTER THE HEIGHT OF THE VERTICAL TAIL , M ", HK INPUT "ENTER THE LEVER OF HORIZONTAL TAIL (1/4 SAH - 1/4 V T ) , M ", LV INPUT "ENTER THE LEVER OF VERTICAL TAIL (Ct - 1/2 H v o) , M ", HV 104 HAF = HFO / 2 + (HF - HFO) LAF = LF / HAF KB = (.32 * (XOF - .25) + .15 / (LF ^ 1.5)) / 10 - .001 LVO = HK ^ 2 / SVO AVO = LVO * .01 + .01 VVO = SVO * LV / SK / RK MYBO = -VVO * AVO: REM MYBO - STAT.THE RESISTANCE INTRODUCED BY THE TAIL MYF = .75 * KB * HF * LF ^ 2 / SK / RK REM MYF - UNSTABLE OF FUSEL IF FAF = 1 OR FAF = 2 OR FAF = 4 THEN MYY = 0 IF FAF = 3 THEN MYY = -.0002 IF FAF = 5 THEN MYY = -.00045 REM MYY - WING AND FUSEL VZAIMOD MYS = MYF + MYBO + MYY IF FAF = 1 OR FAF = 2 OR FAF = 4 THEN V = 1: KINT = -220 IF FAF = 3 THEN V = 2: KINT = -20 IF FAF = 5 THEN V = 4: KINT = 200 MXKR = (-2.17 - .15 * (LAM - 6)) / 10000 * V MXY = KINT * HAF ^ 2 * XK / SK / RK / 10000 HOT = HV / RK SOT = SVO / SK SOTO = SOT / .004 * (PI / 180) MXBO = -HOT * (TAN(SOTO)) * .005 REM - MXBO - THE RESISTANCE INTRODUCED BY THE VERT AIL MXS = MXKR + MXY + MXBO COOT = MXS / MYS: CLS SCREEN 1: VIEW (10, 10)-(300, 180), , 4 COLOR 1 LOCATE 4, 9: PRINT "THE RATIO OF " LOCATE 5, 9: PRINT "THE LATERAL AND DIRECTIONAL " LOCATE 6, 9: PRINT "STATIC STABILITY OF THE AIRCRAFT" COOTT = (INT(COOT * 100)) / 100 LOCATE 8, 15: PRINT "MX/MY="; COOTT LOCATE 10, 9: PRINT "RECOMENDED > 0.7-1.0" LOCATE 12, 9: PRINT "-----------------------" 109 MYWYW = -2 * AVO * (SVO / SK) * (LV / RK) ^ 2 * .85 ZU = SQR(1 / 3) KI = .063 + .03 * LAM MYWYK = -ZU ^ 2 / 2 * ((A * Y(11) ^ 2) - Y(11) * (CYA / PI / LAM - 1)) * 6 * KI MYWYF = .2 * MYWYW MYWY = MYWYW + MYWYK + MYWYF JY = GS1 / 12 * (RK ^ 2 + LF ^ 2) * .8 TZY = JY / MYWY / QQQ / SK / RK TZ = (INT(TZY * 100)) / 100 LOCATE 14, 9: PRINT "DYNAMIC STABILITY OF AIRPLANE" LOCATE 16, 9: PRINT "THE DECAY TIME, SEC ="; -TZ LOCATE 16, 27: PRINT "<=1.5" LOCATE 18, 9: PRINT "THE DECAY TIME " LOCATE 19, 9: PRINT "OF SHORT-PERIODIC LATERAL" LOCATE 20, 16: PRINT "MOVEMENT" SLEEP 7 LOCATE 22, 9: INPUT "END-0:REPEAT-1:BEGIN-2"; ASK IF ASK = 0 THEN GOTO 117 IF ASK = 1 THEN CLS: GOTO 100 IF ASK = 2 THEN GOTO 1 117 STOP: REM END OF PROGRAMM -ALT-ENTER-EXIT