A Critical Assessment of Wind Tunnel Results for the NACA 0012 Airfoil

reportActive / Technical Report | Accession Number: ADA193182 | Open PDF

Abstract:

A large body of experimental results, which were obtained in more than 40 wind tunnels on a single, well-known two dimensional configuration, has been critically examined and correlated. An assessment of some of the possible sources of error has been made for each facility, and data which are suspect have been identified. It was found that no single experiment provided a complete set of reliable data, although one investigation stands our as superior in many respects. However, from the aggregate of data the representative properties of the NACA 0012 airfoil can be identified with reasonable confidence over wide ranges of Mach number, Reynolds number, and angles of attack. This synthesized information can now be used to assess and validate existing or future wind tunnel results and to evaluate advanced Computational Fluid Dynamics code.

Author(s):
Mccroskey, W. J.
Author Organization(s):
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES RESEARCHCENTER
Descriptive Note:
Technical memo.
Pagination:
0024

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
NASA-A-87321, NASA-TM-100019
Monitor Series:
TM-100019, TR-87-A-5, NASA-A
 Subject Terms
Joint Capability Areas:
JCA_3.2_Engagement; JCA_3_Force Application; JCA_3.2.1_Kinetic Means; JCA_1.2.7_Experimentation; JCA_5_Command and Control; JCA_5.3_Planning; JCA_1_Force Support; JCA_1.2_Force Preparation
Modernization Areas:
Directed Energy
Communities of Interest:
Space
Descriptor(s):
*AIRFOILS, *WIND TUNNELS, SOURCES, SYNTHESIS, TWO DIMENSIONAL, ANGLE OF ATTACK, RELIABILITY, CONFIGURATIONS, ERRORS, AERODYNAMIC CHARACTERISTICS, MACH NUMBER, RANGE(EXTREMES), REYNOLDS NUMBER
Field(s)/Group(s):
Aircraft, Fluid Mechanics
Report Date:
1987 Oct 01