Effects of Aspect Ratio on Air Flow at High Subsonic Mach Numbers

Abstract

Schlieren photographs were used in an investigation to determine the effects of changing the aspect ratio from infinity to 2 on the air flow past a wing at high subsonic Mach numbers. The results indicated that the decreased effects of compressibility on drag coefficients for the finite wing are produced by a reduction in the compression shock and flow separation.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1952
Accession Number
ADA377167

Entities

People

  • Milton D. Humphreys
  • W. F. Lindsey

Organizations

  • National Aeronautics and Space Administration

Tags

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Air Flow
  • Aspect Ratio
  • Boundary Layer
  • Coefficients
  • Compression
  • Flow
  • Flow Separation
  • Free Stream
  • Mach Number
  • Photographs
  • Reynolds Number
  • Shock
  • Shock Waves
  • Two Dimensional
  • Two Dimensional Flow

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.