Transonic Wind-Tunnel Investigation of the Static Longitudinal Aerodynamic Characteristics of Several Configurations of the Scout Vehicle and of a Number of Related Models

Abstract

Tests were conducted in the Langley 8-foot transonic pressure tunnel at Mach numbers from 0.40 to 1.20 and Reynolds numbers per foot of approximately 3.8 x 10 to the 6th power to determine the static longitudinal aerodynamic characteristics of a 1/15-scale model of the Scout vehicle and of several related configurations. Results are presented which show, for various models, the effects of fin planform, protuberances, an afterbody flare, and a variation in second-stage transition-flare angle.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1961
Accession Number
AD0255526

Entities

People

  • Thomas C. Kelly

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Afterbodies
  • Aspect Ratio
  • Bodies
  • Coefficients
  • Dynamic Pressure
  • Flared Afterbodies
  • Free Stream
  • Mach Number
  • Models
  • Nose Cones
  • Planform
  • Reconnaissance Vehicles
  • Reynolds Number
  • Scale Models
  • Static Pressure
  • Three Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.