This software package contains three programs which compute geometric, mass, aerodynamic, and structural characteristics of fighter type aircraft. The programs were developed for computational support of a parametric study of planform and aeroelastic effects on aerodynamic center and stability derivatives. They calculate alpha- and q- stability derivatives and induced drag for thin elastic aeroplanes at subsonic and supersonic speeds. The programs are applicable to studies of steady state aeroelastic effects on stability characteristics of airplanes, but results are limited in validity to wings of typical fighter airplanes with a weight of 40,000 pounds (178,000 Newtons) and wing structures designed to withstand a limit load of 7.33 g's.

The programs represent the airplane at subsonic and supersonic speeds as thin surface(s) (without dihedral) composed of discrete panels of constant pressure for the aerodynamic effects, and as slender beam(s) for the structural effects. They compute the static aeroelastic angle-of-attack and pitch rate stability derivatives for a twisted and cambered thin airplane configuration at various flight conditions. ( Kansas Univ. )

This program was released by NASA through COSMIC as LAR-11602. The italicized text above is from the official NASA release.

- Go to the page of references for the Static Aeroelastic program.
- Download elastic.zip, containing the original source code for the three programs. These programs require the Control Data extensions to Fortran of OPENMS, READMS, and WRITMS and I will not be able to get this running until I get the modern equivalents into the programs.