Airfoil Profile Drag

reportActive / Technical Report | Accession Number: ADA017321 | Open PDF

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.

Author(s):
Schwartzberg, Milton A.
Author Organization(s):
ARMY AVIATION SYSTEMS COMMAND ST LOUIS MO
Descriptive Note:
Final rept.
Supplementary Note:
DOI: 10.21236/ADA017321
Pagination:
0039

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release
Distribution Statement:
Approved For Public Release; Distribution Is Unlimited.

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
USAAVSCOM-TR-75-19
Project Number(s):
DA-1-F-262209-AH-76
Monitor Series:
USAAMRDL/CA
 Subject Terms
Joint Capability Areas:
JCA_5_Command and Control; JCA_5.3_Planning; JCA_6.4.1_Secure Information Exchange; JCA_6_Net Centric; JCA_6.4_Information Assurance
Communities of Interest:
Air Platforms
Descriptor(s):
*AIRFOILS, *DRAG, ARMY AIRCRAFT, COEFFICIENTS, ESTIMATES, METHODOLOGY, SUBSONIC CHARACTERISTICS, SURFACE PROPERTIES, TURBULENT BOUNDARY LAYER
Field(s)/Group(s):
Aerodynamics, Fluid Mechanics
Keyword(s):
SMOOTH BODIES
Report Date:
1975 Jun 01