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

Question

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

(a) Calculate the lift coefficient for level flight at H = 33000f t with VCAS = 290kt. 1

(b) Calculate the drag coefficient and drag at the same condition.

(c) Using stall speed, find the maximum lift coefficient CLmax at H = 35000f t.

(d) Plot the CL ? CD graph for CL ? [0, CLmax].

for aircraft.opf: https://www.zeta-uploader.com/tr/browse/1965299629

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

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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