Using BADA3.11 user manual and aircraft.OPF file, solve the problems given below.

(a) Assume that geopotential pressure altitude (Hp) equals to geopotential altitude (H) and assume ISA conditions (?T = 0). Then, calculate maximum climb and take-off thrust according to altitude. Write a Matlab function (f(H)) that gives the maximum climb and take-off thrust. Plot the H ? Tclimb graph for climb phase for H ? [0, 35000f t].

(b) Calculate descent thrust according to altitude. Write a Matlab function (f(H)) that gives the descent thrust. Take the Hp,des = 8000f t and only use CT des,high and CT des,low in calculation. Plot the H ? Tdescent graph for descent phase for H ? [0, 35000f t].

https://www.eurocontrol.int/sites/default/files/field_tabs/content/documents/sesar/user-manual-bada-3-12.pdf

Here is the 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 /