Accession Number:

ADA017321

Title:

Airfoil Profile Drag

Descriptive Note:

Final rept.

Corporate Author:

ARMY AVIATION SYSTEMS COMMAND ST LOUIS MO

Personal Author(s):

Report Date:

1975-06-01

Pagination or Media Count:

39.0

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.

Subject Categories:

  • Aerodynamics
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE