Accession Number:

ADA028794

Title:

Hypersonic Aeroelastic Analysis

Descriptive Note:

Final rept.

Corporate Author:

LOCKHEED MISSILES AND SPACE CO INC SUNNYVALE CA

Report Date:

1975-09-30

Pagination or Media Count:

220.0

Abstract:

The aerothermoelastic characteristics of a tactical missile operating at near zero angle of attack in the low hypersonic speed range have been studies. An integrated digital computer program has been developed for the aeroelastic response of sharp-edge aerodynamically heated, cantilevered lifting surfaces representative of tactical missile fins. The nonuniform flow generated by a spherically blunted missile nose is accounted for. Based upon the application of the computer program to selected cases, recommendations are made regarding the analysis procedures. Appropriate prestress conditions are obtained from the quasi-static solution. An analytic theory is developed which can predict the nonuniform flow effects of nose bluntness in the complete hypersonic speed range up to Mach 3.

Subject Categories:

  • Guided Missiles
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE