NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Performance of two transonic airfoil wind tunnels utilizing limited ventilationA limited-zone ventilated wall panel was developed for a closed-wall icing tunnel which permitted correct simulation of transonic flow over model rotor airfoil sections with and without ice accretions. Candidate porous panels were tested in the Ohio State University 6- x 12-inch transonic airfoil tunnel and result in essentially interference-free flow, as evidenced by pressure distributions over a NACA 0012 airfoil for Mach numbers up to 0.75. Application to the NRC 12- x 12-inch icing tunnel showed a similar result, which allowed proper transonic flow simulation in that tunnel over its full speed range.
Document ID
19850003712
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lee, J. D.
(Ohio State Univ. Columbus, OH, United States)
Gregorek, G. M.
(Ohio State Univ. Columbus, OH, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1984
Publication Information
Publication: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983
Subject Category
Aerodynamics
Accession Number
85N12020
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Document Inquiry

Available Downloads

There are no available downloads for this record.
No Preview Available