Airfoil Profile Drag

Abstract

A method is presented for the estimation of the profile drag coefficient of airfoils at subsonic Mach numbers below the drag rise values. The method is applicable to smooth airfoils, with fully turbulent boundary layers, at any Reynolds number. The method is simple to apply for rapid estimation purposes, and to incorporate into an aircraft performance computation procedure.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1975
Accession Number
ADA017321

Entities

People

  • Milton A. Schwartzberg

Organizations

  • United States Army Aviation and Missile Command

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Aircrafts
  • Boundary Layer
  • Boundary Layer Transition
  • Dynamic Pressure
  • Fixed Wing Aircraft
  • Free Stream
  • Laminar Flow
  • Leading Edges
  • Mach Number
  • Pressure Distribution
  • Reynolds Number
  • Rotary Wing Aircraft
  • Skin Friction
  • Transitions
  • Turbulent Boundary Layer
  • Turbulent Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Approximation Theory.