Results of Flight Tests at Supersonic Speeds to Determine the Effect of Body Nose Fineness Ratio on Body and Wing Drag

Abstract

Supersonic rocket-powered, winged, and wingless models were tested to Mach 1.4 to determine effect of nose fineness ratio on total and component drag. Winged models with and without sweepback were tested. Results show that increased nose fineness ratio increased wing-body drag near Mach 1.0 but decreased total drag at higher Mach. Increased fineness ratio decreased drag of wingless bodies. Wing drag values change with installation on different body shapes.

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Document Details

Document Type
Technical Report
Publication Date
Jun 26, 1947
Accession Number
ADA800563

Entities

People

  • Ellis R. Katz

Organizations

  • Langley Research Center

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Aeronautics
  • Aircrafts
  • Aspect Ratio
  • Bodies
  • Coefficients
  • Data Reduction
  • Drag
  • Drag Reduction
  • Fineness Ratio
  • Instrumentation
  • Intact Stability
  • Mach Number
  • Shape
  • Standards
  • Swept Wings

Fields of Study

  • Agricultural and Food sciences
  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow