DESIGN ANALYSIS SUMMARY OF TWO FORCE-BALANCE HYPERSONIC INLET CONFIGURATIONS,

Abstract

Two hypersonic inlet models were designed for force balance testing in the Cornell Aeronautical Laboratory 48-inch shock tunnel over a Mach Number range of 8 to 16. The performance of these models is to be established experimentally on the basis of their measured internal drag. Reasons for considering this method of establishing hypersonic inlet performance and use of the associated drag equivalent pressure recovery are discussed. The design of these models, the resulting inlet geometry, and the related performance caluclations are described. (Author)

Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1964
Accession Number
AD0437909

Entities

People

  • George K. Richy
  • Paul H. Kutschenreuter Jr.
  • Richard L. Balent

Organizations

  • Flight Dynamics Laboratory

Tags

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Buildings And Structures
  • Geometry
  • Induction Systems
  • Mach Number
  • Recovery
  • Research Facilities
  • Shock Tunnels
  • Test Facilities

Fields of Study

  • Physics

Readers

  • Business Analytics
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow