Accession Number : ADA111997

Title :   Aerodynamic Computer Code for Analyzing Heat Transfer and Pressure Loads on Missiles.

Descriptive Note : Final rept. 12 Sep 80-11 Mar 82,

Corporate Author : MCDONNELL DOUGLAS ASTRONAUTICS CO HUNTINGTON BEACH CA

Personal Author(s) : Wang,Kenneth K ; Weatherford,R H

PDF Url : ADA111997

Report Date : Mar 1982

Pagination or Media Count : 84

Abstract : An aerodynamic computer code was developed for calculating the pressure distribution on a missile or its components, e.g., body and wings and subsequently interpolating the results by surface fit at locations as specified for structural analysis using the NASTRAN computer code. The code is valid from subsonic up to high supersonic speeds and for generalized attitudes of the missile. Subroutines have been added to the code to enable calculation of temperature histories, equilibrium temperature and heat flux at arbitrary locations on a missile. In addition, capability for treating slightly blunted nose configurations has been incorporated. (Author)

Descriptors :   *Aerodynamic loading, *Heat transfer, *Pressure distribution, *Guided missiles, Structural analysis, Computations, Computer programming, Wing body configurations, Transonic characteristics, Aerodynamic heating, Nose tips, Blunt bodies, Heat flux, Computerized simulation, Output, Tables(Data)

Subject Categories : Guided Missiles
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE