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Record Details

Record 63 of 5392
Performance of two transonic airfoil wind tunnels utilizing limited ventilation
Offline Availability: Go to Request Form
Author and Affiliation:
Lee, J. D.(Ohio State Univ., Columbus, OH, United States)
Gregorek, G. M.(Ohio State Univ., Columbus, OH, United States)
Abstract: A 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.
Publication Date: Jan 01, 1984
Document ID:
19850003712
(Acquired Nov 13, 1995)
Accession Number: 85N12020
Subject Category: AERODYNAMICS
Document Type: Conference Paper
Publication Information: NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983; p 165-170
Publisher Information: United States
Financial Sponsor: NASA; United States
Organization Source: Ohio State Univ.; Columbus, OH, United States
Description: 6p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: AIRFOILS; PANELS; PRESSURE DISTRIBUTION; SUBCRITICAL FLOW; SUPERCRITICAL FLOW; TRANSONIC FLOW; VENTILATION; WALLS; HIGH REYNOLDS NUMBER; MACH NUMBER; SIMULATION; TRANSONIC WIND TUNNELS; WIND TUNNEL TESTS
Imprint And Other Notes: In NASA. Langley Research Center Wind Tunnel Wall Interference Assessment and Correction, 1983 p 165-170 (SEE N85-12011 03-02)
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