Publication Date:
2011-08-24
Description:
For prescribed aircraft flight conditions of weight, length, Mach number and altitude, and front area balance point this program calculates the Whitman F function and the corresponding equivalent area distribution that minimize over pressure or minimum shock pressure signature utilizing the method of Seebass and George (Cornell University). The solution procedure is based upon equations for (1) the total area growth necessary for flight conditions, (2) location of the front area balancing point, (3) location of the rear area balancing point, (4) ratio of the front to rear shock, and (5) the intersection of the F function with the rear area balancing line at the rear balancing point. These five equations reduce to nonlinear equations in two unknowns which are solved iteratively using the Newton-Raphson method and a combination of the secant and bisection methods. The program is written in CDC FORTRAN IV (Version 2.3) and has been implemented on a CDC 6600 computer under the SCOPE operating system with a memory requirement of approximately 110K (octal) of 60 bit words.
Keywords:
AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Type:
LAR-11979
Format:
text
