TRANSONIC DYNAMIC LONGITUDINAL STABILITY CHARACTERISTICS OF SIX BALLISTIC REENTRY CONFIGURATIONS DESIGNED FOR SUPERSONIC IMPACT

Abstract

An investigation has been made in the Langley 8-foot transonic pressure tunnel to determine the damping-in-pitch and the oscillatory longitudinal stability characteristics of six bluntnose cylinder-flare reentry configurations that were designed for supersonic impact. Tests were made at Mach numbers from 0.80 to 1.15 and at mean angles of attack from 0 to 14 degrees. Reynolds numbers, based on 0.333 foot, varied from 0.62 to 0.69 times 10 to the 6th power. The amplitude of the forced oscillation was 2 degrees with reduced frequencies from 0.012 to 0.036. Some of the effects of flare angle, nose shape, and fins are noted.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1962
Accession Number
AD0328597

Entities

People

  • Ernest R. Hillje
  • Robert A. Kilgore

Organizations

  • Langley Research Center

Tags

DTIC Thesaurus Topics

  • Aeronautics
  • Air Flow
  • Air Force
  • Air Force Facilities
  • Bodies
  • Boundary Layer
  • Diameters
  • Flow
  • Free Stream
  • Frequency
  • Government Procurement
  • High Angles
  • Mach Number
  • Oscillation
  • Reynolds Number
  • Stagnation Temperature
  • Turbulent Boundary Layer

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow