Accession Number:

AD0686738

Title:

THE INFLUENCE OF SHOCK WAVE-BOUNDARY LAYER EFFECTS ON THE DESIGN OF HYPERSONIC AIRCRAFT

Descriptive Note:

Technical rept. Jan-Jul 1967

Corporate Author:

AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH

Report Date:

1969-03-01

Pagination or Media Count:

54.0

Abstract:

The design of aircraft for sustained operation at hypersonic speeds requires the understanding of aerodynamic heating generated through interfering flow fields. Such interactions not only determine the required level of vehicle thermal protection but also create severe gradients of temperature along skin panels. An extensive experimental program supporting the conceptual design of these vehicles was completed. Experimental results were generated on models illuminating the basic features of both two- and three-dimensional interactions with results applicable to the design of hypersonic aircraft. The report presents these data and correlations with theory in the Mach number range 6 through 10. Results indicate the applicability of current design practices, areas requiring further investigation, and the problems involved in interpretation and application of interference data from hypersonic facilities to the desired free flight condition.

Subject Categories:

  • Aerodynamics
  • Aircraft
  • Fluid Mechanics
  • Thermodynamics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE