Record Details

Effects of Cone Angle, Mach Number, and Nose Blunting on Transition at Supersonic Speeds
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Author and Affiliation:
Czarnecki, K. R.(NASA Langley Research Center, Hampton, VA, United States);
Jackson, Mary W.(NASA Langley Research Center, Hampton, VA, United States)
Abstract: An investigation has been made to determine the transition characteristics of a group of blunt cones which varied in included apex angle from 27 deg to 60 deg over a Mach number range from 1.61 to 2.20 and a range of tunnel Reynolds number per foot from about 1.5 x 10(exp 6) to 8.0 x 10(exp 6). The tests were made at zero angle of attack and with zero heat transfer. The results indicate that the general level of transition Reynolds number based on boundary-layer momentum thickness and local flow conditions just outside the boundary layer varied between 600 and 1,100. Changes in Mach number had little effect on transition distance and transition Reynolds number for the near-sharp or very small bluntnesses. The effect of Mach number variation on the larger hemispherical bluntnesses was much stronger, with the strongest Mach number effect occurring for Mach numbers between 1.61 and 1.82. With an increase in nose radius, there was a strong decrease in transition distance and transition Reynolds number at the lower Mach numbers. This adverse effect tended to become weaker with increase in Mach number. An increase in cone angle at a constant Mach number caused a reduction in transition distance and transition Reynolds number for the blunt configurations which had approximately the same values of nose radius.
Publication Date: Jan 01, 1961
Document ID:
20040006462
(Acquired Jan 23, 2004)
Subject Category: AERODYNAMICS
Report/Patent Number: NASA-TN-D-634
Document Type: Technical Report
Financial Sponsor: NASA; Washington, DC, United States
Organization Source: NASA Langley Research Center; Hampton, VA, United States
Description: 32p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: CONES; MACH NUMBER; GEOMETRY; REYNOLDS NUMBER; WIND TUNNEL TESTS; SUPERSONIC SPEED; ZERO ANGLE OF ATTACK; SUPERSONIC WIND TUNNELS; BOUNDARY LAYERS
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