Gust-Tunnel Investigation of a 45 deg Sweptforward-Wing Model

Abstract

The results of tests made in the Langley gust tunnel on a 45 deg swept- forward-wing model show that the acceleration increment obtained in a gust can be satisfactorily predicted from a slope of the lift curve obtained by multiplying the slope of the lift curve of the equivalent straight wing by the cosine of the angle of sweep and by using strip theory to estimate the penetration effect.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1948
Accession Number
ADA380900

Entities

People

  • Harold B. Pierce

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aeronautical Laboratories
  • Aircrafts
  • Airplanes
  • Aspect Ratio
  • Center Of Gravity
  • Experimental Data
  • Flight
  • Gust Loads
  • Gusts
  • Leading Edges
  • Steady Flow
  • Swept Wings
  • Sweptback Wings
  • Sweptforward Wings

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Approximation Theory.