xytl.m

飞行高度需在计算初设定

% No.01
% 飞行性能计算－需用推力
% 平飞需用推力的计算
clc;
clear;

disp(' ');
disp('%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%');
disp('%  飞行性能计算－平飞性能计算  %');
disp('%  ★空军工程大学<>工程学院★  %');
disp('%  王晓东◎版权所有 2005年3月  %');
disp('%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%');
disp(' ');

G = 8150.0;
S = 23.0;
H = 12000.0;
% K = [7.478, 8.240, 8.032, 7.239, 5.992, 3.488, 2.349, 2.100, 1.861, 1.657, 1.476, 1.324, 1.193, 1.081];

TCx0 = [
    0.013478
    0.013493
    0.013507
    0.013524
    0.014611
    0.025896
    0.034436
    0.034441
    0.031589
    0.030538
    0.029696
    0.029255
    0.028396
    0.027771
    0.027273
    0.026845];
TAi = [
    0.206530
    0.206289
    0.206047
    0.205806
    0.205560
    0.209018
    0.223322
    0.244748
    0.267197
    0.290234
    0.313367
    0.336425
    0.359560
    0.382798
    0.406161
    0.429703];

H = input('请输入一个高度值(0m~20000m)：');
[T,P,D,A] = GetAir(H);

M = 0.5:0.1:2.0;
V = M * A;

Cy = 2.0*9.8*G./(D*S*V.^2);

Cx0 = interp1(0.5:0.1:2.0, TCx0, M);
Ai = interp1(0.5:0.1:2.0, TAi, M);

Cx = Cx0 + Ai.*Cy.^2;

K = Cy./Cx;

P = G./K;

plot(M, P, '-k');
xlabel('Ma');
ylabel('P/kgf');
% legend([num2str(H) 'm高度需用推力']);
grid on;