Boundary Layer Transition at Supersonic Speeds

Boundary Layer Transition at Supersonic Speeds PDF

Author: E. R. Van Driest

Publisher:

Published: 1961

Total Pages: 108

ISBN-13:

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Experiments carried out in the 12-inch supersonic wind tunnel to investigate the effect of three dimensional roughness elements (spheres) on boundary-layer transition on a 10-degree (apex angle) cone without heat transfer are described. The local Mach number for these tests was 2.71. The data show clearly that the minimum (effective) size of trip required to bring transition to its lowest Reynolds number varies power of the distance from the apex of the cone to the trip. Use of available data at other Mach numbers indicates that the Mach number influence for effective tripping is taken into account by a simple expression. Some remarks concerning the roughness variation for transition on a blunt body are made. Finally, a general criterion is introduced which gives insight to the transition phenomenon and anticipates effects of external and internal disturbances, Mach number transfer.

Boundary-layer Transition Study of Several Pointed Bodies of Revolution at Supersonic Speeds

Boundary-layer Transition Study of Several Pointed Bodies of Revolution at Supersonic Speeds PDF

Author: William A. Cassels

Publisher:

Published: 1970

Total Pages: 76

ISBN-13:

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Boundary-layer transition by the sublimation and impact-pressure techniques and force tests have been performed on three Haack-Adams bodies of revolution of fineness ratios 7, 10, and 13 at zero angle of attack for free-stream Mach numbers of 2.00, 2.75, and 4.63 and a range of Reynolds numbers based on model length of 6 to 15 X 10(to the 6 power) with and without a roughness strip. The grit method of inducing turbulence was found to provide for a nearly complete turbulent flow over the models at the lower Mach numbers and higher Reynolds numbers considered in this study while the amount of trip drag was less than 8 percent of the model drag with transition fixed. A method of interpreting sublimation data was discussed and used and the results compared well with the impact-pressure results.

Some Effects of Leading-edge Sweep on Boundary-layer Transition at Supersonic Speeds

Some Effects of Leading-edge Sweep on Boundary-layer Transition at Supersonic Speeds PDF

Author: Gary T. Chapman

Publisher:

Published: 1961

Total Pages: 1

ISBN-13:

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The effects of crossflow and shock strength on transition of the laminar boundary layer behind a swept leading edge have been investigated analytically and with the aid of available experimental data. An approximate method of determining the crossflow Reynolds number on a leading edge of circular cross section at supersonic speeds is presented. The applicability of the critical crossflow criterion described by Owen and Randall for transition on swept wings in subsonic flow was examined for the case of supersonic flow over swept circular cylinders. A wide range of applicability of the subsonic critical values is indicated. The corresponding magnitude of crossflow velocity necessary to cause instability on the surface of a swept wing at supersonic speeds was also calculated and found to be small. The effects of shock strength on transition caused by Tollmien-Schlichting type of instability are discussed briefly. Changes in local Reynolds number, due to shock strength, were found analytically to have considerably more effect on transition caused by Tollmien-Schlichting instability than on transition caused by crossflow instability. Changes in the mechanism controlling transition from Tollmien-Schlichting instability to crossflow instability were found to be possible as a wing is swept back and to result in large reductions in the length of laminar flow. (Author).

Factors Affecting Transition at Supersonic Speeds

Factors Affecting Transition at Supersonic Speeds PDF

Author: K. R. Czarnecki

Publisher:

Published: 1953

Total Pages: 22

ISBN-13:

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This paper surveys the available material and summarizes what is known to date about boundary-layer transition at supersonic speeds. Variables studied include Mach number, Reynolds number, pressure gradients, heat transfer, surface roughness, and angle of attack. The discussion is limited to bodies of revolution because similar reliable data for wings is lacking.

Boundary-layer Transition Results from the F-16XL-2 Supersonic Laminar Flow Control Experiment

Boundary-layer Transition Results from the F-16XL-2 Supersonic Laminar Flow Control Experiment PDF

Author: Laurie A. Marshall

Publisher:

Published: 1999

Total Pages: 58

ISBN-13:

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A variable-porosity suction glove has been flown on the F-16XL-2 aircraft to demonstrate the feasibility of this technology for the proposed High-Speed Civil Transport (HSCT). Boundary-layer transition data have been obtained on the titanium glove primarily at Mach 2.0 and altitudes of 53,000-55,000 ft. The objectives of this supersonic laminar flow control flight experiment have been to achieve 50- to 60-percent-chord laminar flow on a highly swept wing at supersonic speeds and to provide data to validate codes and suction design. The most successful laminar flow results have not been obtained at the glove design point (Mach 1.9 at an altitude of 50,000 ft). At Mach 2.0 and an altitude of 53,000 ft, which corresponds to a Reynolds number of 22.7 multiplied by 10[factor 6], optimum suction levels have allowed long runs of a minimum of 46-percent-chord laminar flow to be achieved. This paper discusses research variables that directly impact the ability to obtain laminar flow and techniques to correct for these variables.

Boundary-layer Transition at Supersonic Speeds

Boundary-layer Transition at Supersonic Speeds PDF

Author: George M. Low

Publisher:

Published: 1956

Total Pages: 35

ISBN-13:

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The effects of leading-edge blunting on two-dimensional surfaces and surface cooling can be predicted adequately by existing theories, at least in the moderate Mach number range.

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