Effects of Compressibility on the Maximum Lift Characteristics and Spanwise Load Distribution of a 12-Foot-Span Fighter Type Wing of NACA 230 Series Airfoil Sections

Abstract

Lift characteristics and pressure distribution for a NACA 230 wing were investigated for an angle of attack range of from -10 to +24 degrees and Mach range of from 0.2 to 0.7. Maximum lift coefficient increased up to a Mach number of 0.3, decreased rapidly to a Mach number of 0.55, and then decreased moderately. At high speeds, maximum lift coefficient was reached at from 10 to 12 degrees beyond the stalling angle. In high-speed stalls, resultant load underwent a moderate shift outward.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1945
Accession Number
ADA800618

Entities

People

  • A. J. Evans
  • E. O. Pearson Jr.
  • F. E. West Jr.

Organizations

  • Langley Research Center

Tags

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aeronautical Laboratories
  • Aeronautics
  • Aircrafts
  • Airplanes
  • Compressive Properties
  • Dynamic Pressure
  • Fighter Aircraft
  • Flow
  • Fluid Dynamics
  • Load Distribution
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Stalling
  • Static Pressure
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Mathematics or Statistics