The Influence of Heat Transfer on the Drag of Airfoils.

Abstract

An experimental and theoretical study was performed to determine the effects of surface temperature on the drag of airfoils. Models of an aft-loaded profile and of a NACA 65A413 were tested with separate models providing pressure distributions and drag data from cooling or heating at a Mach number of 0.4 and Reynolds number of 2,500,000. Simultaneously an airfoil boundary layer analysis was performed using available theories and empirical correlations for laminar, transitional and turbulent boundary layers. Cooling was found to provide a lower drag and heating a higher value, as expected, for both profiles and the reduction by cooling was substantial for the aft-loaded profile at the condition tested. The measurements agreed well with the theoretical predictions which may then be used to evaluate the effects of both heat transfer and pressure gradients on airfoil transition and drag. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1981
Accession Number
ADA098822

Entities

People

  • John D. Lee

Organizations

  • Ohio State University

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Boundary Layer
  • Drag Reduction
  • Engineering
  • Flow Fields
  • Heat Transfer
  • Mach Number
  • Measurement
  • Photographs
  • Pressure Distribution
  • Pressure Gradients
  • Stagnation Temperature
  • Supercritical Flow
  • Surface Temperature
  • Test Facilities
  • Turbulent Flow
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion and Flow Dynamics.