aerostd.c

多学科优化软件isight培训教程初级pdf有很详细的例子讲解

#include <stdio.h>
#include <math.h>

void GetInputs (double *b, double *Swing, double *Lfuse, double *Dfuse) {

/* Prompt User for Inputs from the Terminal */

printf("\nWing Span (ft)                 b  = ");
scanf("%lf", b);
printf("Surface Area of the Wing    Swing = ");
scanf("%lf", Swing);
printf("Length of Fuselage          Lfuse = ");
scanf("%lf", Lfuse);
printf("Diameter of Fuselage        Dfuse = ");
scanf("%lf", Dfuse);
};

void main() {
	
double b;
double AR; 
double Swing;
double Lfuse;
double Dfuse;
double Afuse;
double Swetted;
double LoverD;
double pi;
double tail;
double cone;
double cyl;
int i=1;

/* Get Inputs */

GetInputs(&b,&Swing,&Lfuse,&Dfuse);

/* wetted area calculation */

AR=(b*b)/Swing; 
pi=4.0*atan(1.0);

cyl = (pi * Dfuse * 0.6*Lfuse);
cone = (pi * pow((Dfuse/2.0),2) * 0.4*Lfuse) / 3.0;

Afuse= cyl + cone + pi*pow((Dfuse/2.0),2);
tail= 4*(1.25*Dfuse)*(0.125*Lfuse) + 2*(1.5*Dfuse)*(0.15*Lfuse);
Swetted=Afuse + 2.0*Swing - 2.0*Dfuse*(Swing/b) + tail;

/* estimate lift to drag ratio at cruise */

LoverD= 10.0 + 4.0*(AR/(Swetted/Swing)-1.0);

if (LoverD > 16 ) { 
   LoverD=16.0; 
}

/* Print Outputs to Screen */

printf("\n");
printf(" ==== Aerodynamic Analysis Output File ==== \n");
printf("\n");
/* printf("Aspect Ratio of the Wing     = %-15.6G\n", AR); */
printf("Surface Area of the Fuselage = %-15.6G  ft^2\n", Afuse);
printf("Wetted Area of the Aircraft  = %-15.6G  ft^2\n", Swetted);
printf("Lift/Drag of the Aircraft    = %-15.6G\n", LoverD);

exit (0);
}