Reference Code:

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% Date: 01/10/2018

% Author: Ali Jhemi

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% Script file name: drive_thrust.m

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% Given AC aerpdynamic data, this script computes the thrust required

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% Script associated with section 6.3 Anderson

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% Clear workspace, command window, and figures

clear all % clear workspace,

clc % clear command window

clf % clear figures

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% AC aerodynamic parameters:

W = 2950; % Weight of AC in lb

Roh = 0.002377; % Sea level air density lb/ft3

S = 174; % Wing Area ft2

b = 35.8; % Wingspan ft

AR = b^2/S; % Aspect ratio

CD0 = 0.025; % Parasite drag coefficient

e = 0.8; % Oswald efficiency factor

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% Five steps from pp 450- 451

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% Step 1: Choose AC airspeed (ft/s)

Vinf = 200;

% Step 2: Compute Coefficient of lift

CL = W/(0.5*Roh*Vinf^2*S);

% Step 3: Compute CD

CD = CD0 + CL^2/(pi*e*AR);

% Step 4: Compute Lift to Drag ratio

LDR = CL/CD;

% Step 5: Compute Thrust required

TR = W/LDR;

% Store sesults in string S (C-language syntax: very flaxibale)

S = sprintf('\t Vinf \t TR');

disp(S);

S = sprintf('%10.2f \t\t %10.3f',Vinf,TR);

% Display results

disp(S);

plot(Vinf,TR,'*');

xlabel('Velocity (ft/s)')

ylabel('Thrust required (lb)')

title('Thrust required vs airspeed')

grid

% end script

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Given the Aerodynamic characteristics of the CP-1 AC and assume sea level conditions Wingspan 35.8 ft Wing area = 174 ft2 Normal gross weight = 2950 lb Fuel capacity: 65 gal of aviation gasoline Power plant: one-piston engine of 230 hp at sea level Specific fuel consumption = 0.45 lb/(hp)(h) Parasite drag coefficient C 0.025 Oswald efficiency factor e=0.8 Propeller efficiency = 0.8 1. Write a well commented Matlab script that does the following: For the interval of airspeeds (Vinf) starting from Vmin = 80 ft/s, stopping at Vmax = 400t/s, computer the Thrust required (TR) at 5 ft/s increment. 2. Print results in a table format for the first 10 airspeeds. First column contains the airspeed and the second contains TR 3. Plot the results on a figure with: Title, xlabel, and ylabel Assuming airspeed below the Drag divergent Mach number and that the trust available from the AC engine is 700 lb,. From the graph, read: 4. Maximum airspeed that the CP-1 can attain? 5. Airspeed that yields the minimum thrust required Given the Aerodynamic characteristics of the CP-1 AC and assume sea level conditions Wingspan 35.8 ft Wing area = 174 ft2 Normal gross weight = 2950 lb Fuel capacity: 65 gal of aviation gasoline Power plant: one-piston engine of 230 hp at sea level Specific fuel consumption = 0.45 lb/(hp)(h) Parasite drag coefficient C 0.025 Oswald efficiency factor e=0.8 Propeller efficiency = 0.8 1. Write a well commented Matlab script that does the following: For the interval of airspeeds (Vinf) starting from Vmin = 80 ft/s, stopping at Vmax = 400t/s, computer the Thrust required (TR) at 5 ft/s increment. 2. Print results in a table format for the first 10 airspeeds. First column contains the airspeed and the second contains TR 3. Plot the results on a figure with: Title, xlabel, and ylabel Assuming airspeed below the Drag divergent Mach number and that the trust available from the AC engine is 700 lb,. From the graph, read: 4. Maximum airspeed that the CP-1 can attain? 5. Airspeed that yields the minimum thrust required