Record Details

Boundary-Layer Transition on a Group of Blunt Nose Shapes at a Mach Number of 2.20
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Author and Affiliation:
Jackson, Mary W.(NASA Langley Research Center, Hampton, VA United States);
Czarnecki, K. R.(NASA Langley Research Center, Hampton, VA United States)
Abstract: An investigation has been made to study boundary-layer transition on six axisymmetrical blunt bodies of revolution. Model shapes were selected with respect to the degree of favorable pressure gradient over the model surface. Tests were conducted at a Mach number of 2.20 and over a range of free-stream Reynolds number per foot of about 1.4 x 10(exp 6) to 6.5 x 10(exp 6). The tests were made at an angle of attack of 0 deg. with zero heat transfer. For the hemisphere, the flow remained essentially laminar over the model surface length for the entire pressure range of the tests. For a strong favorable pressure gradient followed by any weak favorable, neutral, or adverse gradient, the tendency was for transition to occur at or immediately behind the shoulder. A single strip of three-dimensional roughness in the region of strong favorable pressure gradient did not fix transition on the models at the roughness location except at the maximum test pressures, whereas a second roughness strip added in a region of neutral or adverse pressure gradient did fix transition. Experimental pressure coefficients agreed closely with modified Newtonian theory except in the shoulder region.
Publication Date: Jul 01, 1961
Document ID:
19980227788
(Acquired Oct 31, 1998)
Subject Category: FLUID MECHANICS AND HEAT TRANSFER
Report/Patent Number: NASA-TN-D-932, L-1383
Document Type: Technical Report
Financial Sponsor: NASA; Washington, DC United States
Organization Source: NASA Langley Research Center; Hampton, VA United States
Description: 26p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: BOUNDARY LAYER TRANSITION; BODIES OF REVOLUTION; HEAT TRANSFER; BLUNT BODIES; WIND TUNNEL TESTS; FREE FLOW; WIND TUNNEL MODELS; REYNOLDS NUMBER; SHAPES; PRESSURE RATIO; SURFACE ROUGHNESS; SURFACE TEMPERATURE; PRESSURE GRADIENTS
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