I really need help this quiestion has to be solved till today pls solve it. Usin

Question

I really need help this quiestion has to be solved till today pls solve it.

Using BADA3.11 user manual and aircraft.OPF le, solve the problems given below. Write necessary
Matlab functions.
(a) Calculate the lift coefficient for level
ight at H = 33000ft with VCAS = 290kt.
(b) Calculate the drag coecient and drag at the same condition.
(c) Using stall speed, nd the maximum lift coecient CLmax at H = 35000ft.
(d) Plot the CL - CD graph for CL 2 [0;CLmax].

aircraft.opf file :

CCCCCCCCCCCCCCCCCCCCCCCCCCCCCC aircraft.OPF CCCCCCCCCCCCCCCCCCCCCCCCCC/
CC /
CC AIRCRAFT PERFORMANCE OPERATIONAL FILE /
CC /
CC /
CC File_name: aircraft.OPF /
CC /
CC Creation_date: Apr 30 2002 /
CC /
CC Modification_date: Dec 19 2008 /
CC /
CC /
CC====== Actype ======================================================/
CD XXXX__ 2 engines Jet M /
CC XXXX-XXX with NA engines wake /
CC /
CC====== Mass (t) ====================================================/
CC reference minimum maximum max payload mass grad /
CD .65300E+02 .41150E+02 .78300E+02 .20300E+02 .26974E+00 /
CC====== Flight envelope =============================================/
CC VMO(KCAS) MMO Max.Alt Hmax temp grad /
CD .34000E+03 .82000E+00 .41000E+05 .34982E+05 -.5410E+02 /
CC====== Aerodynamics ================================================/
CC Wing Area and Buffet coefficients (SIM) /
CCndrst Surf(m2) Clbo(M=0) k CM16 /
CD 5 .12465E+03 .12454E+01 .55567E+00 .00000E+00 /
CC Configuration characteristics /
CC n Phase Name Vstall(KCAS) CD0 CD2 unused /
CD 1 CR Clean .14900E+03 .25452E-01 .35815E-01 .00000E+00 /
CD 2 IC Flap1 .11900E+03 .26200E-01 .44800E-01 .00000E+00 /
CD 3 TO Flap5 .11700E+03 .35700E-01 .42300E-01 .00000E+00 /
CD 4 AP Flap15 .10900E+03 .49200E-01 .42400E-01 .00000E+00 /
CD 5 LD Flap30 .10700E+03 .68900E-01 .40400E-01 .00000E+00 /
CC Spoiler /
CD 1 RET /
CD 2 EXT .00000E+00 .00000E+00 /
CC Gear /
CD 1 UP /
CD 2 DOWN .24900E-01 .00000E+00 .00000E+00 /
CC Brakes /
CD 1 OFF /
CD 2 ON .00000E+00 .00000E+00 /
CC====== Engine Thrust ===============================================/
CC Max climb thrust coefficients (SIM) /
CD .14659E+06 .53872E+05 .30453E-10 .96177E+01 .85132E-02 /
CC Desc(low) Desc(high) Desc level Desc(app) Desc(ld) /
CD .75573E-01 .87412E-01 .95770E+04 .19448E+00 .30610E+00 /
CC Desc CAS Desc Mach unused unused unused /
CD .28000E+03 .78000E+00 .00000E+00 .00000E+00 .00000E+00 /
CC====== Fuel Consumption ============================================/
CC Thrust Specific Fuel Consumption Coefficients /
CD .70057E+00 .10681E+04 /
CC Descent Fuel Flow Coefficients /
CD .14190E+02 .65932E+05 /
CC Cruise Corr. unused unused unused unused /
CD .92958E+00 .00000E+00 .00000E+00 .00000E+00 .00000E+00 /
CC====== Ground ======================================================/
CC TOL LDL span length unused /
CD .23080E+04 .16460E+04 .34300E+02 .39470E+02 .00000E+00 /
CC====================================================================/
FI /

Explanation / Answer

function[CL, CD, CP] = LiftandDrag(t, CLi, CDi) t = 1:100; CDi = 0.01; %Initial canopy Drag Coefficient CLi = 0.0; %Initial canopy Lift Coefficient if t < 5 CL = .2*t+CLi; CD = 0.038*t+CDi; %drag coeffcient of chute CP = 2; %drag of payload elseif t > 5 CL = 1; %Inflated canopy Lift Coefficient CD = .2; %Inflated canopy Drag Coefficient CP = 2; %Payload Drag Coefficient function [CL, CD, CP] = calcLiftAndDrag t = 1:100; CDi = 0.01; %Initial canopy Drag Coefficient CLi = 0.0; %Initial canopy Lift Coefficient [CL, CD, CP] = LiftandDrag(t, CLi, CDi); function[CL, CD, CP] = LiftandDrag(t, CLi, CDi) CL = zeros(size(t)); CD = zeros(size(t)); CP = zeros(size(t)); mask = t

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