Two-Dimensional Subsonic Experiments with an NACA 0012 Airfoil

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Abstract:

Two-dimensional tests were made with a 6-inch chord NACA 0012 section in the Calspan 8-foot Transonic Wind Tunnel to obtain section data with minimum wall interference effects. The measurements included three - component force data, surface pressure distributions and oil flow observations, and were made at Mach numbers ranging from 0.4 to 0.95 and at a chord Reynolds number of 1,000,000. Comparisons of the lift curve data with available theory indicate that the results are within about 1% of being two-dimensional.

Author(s):
Vidal, R. J. ; Catlin, P. A. ; Chudyk, D. W.
Author Organization(s):
CALSPAN CORP BUFFALO NY
Funding Organization(s):
Office of Naval Research, Arlington , VA
Document Type:
Technical Report/Technical Report
Publication Date:
1973 Dec 01
Pagination:
54

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution Code:
A - Approved For Public Release
Distribution Statement: Public Release

RECORD

Collection: TRECMS
Identifying Numbers
Contract Number(s):
N00014-72-C-0102
Project Number(s):
NR 061-199/09-08-71(438)
Subject Terms
Communities of Interest:
Air Platforms
Descriptor(s):
boundary layer, pressure distribution, wind tunnels, new york, corporations, mach number, two dimensional, leading edges, measurement, reynolds number, shock waves, united states, airfoils, aspect ratio, flow, military research, static pressure
Subject Categories:
Test Equipment, Research Facilities and Reprography; Physics
Update Date:
2021 Jul 20