In-flight boundary-layer transition on a large flat plate at supersonic speeds PDF Download
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Author: D. W. Banks
Publisher:
ISBN:
Category :
Languages : en
Pages : 21
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Book Description
Author: D. W. Banks
Publisher:
ISBN:
Category :
Languages : en
Pages : 21
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Book Description
Author: E. R. Van Driest
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 108
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Book Description
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.
Author: Raymond Morton Hicks
Publisher:
ISBN:
Category :
Languages : en
Pages : 52
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Author: William D. Harvey
Publisher:
ISBN:
Category :
Languages : en
Pages : 40
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Author: Bill Harvey
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 40
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Book Description
Author: Michael E. Tauber
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ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 44
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Author: Gary T. Chapman
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 38
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Author: William A. Cassels
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 76
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Book Description
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.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
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Author: Laurie A. Marshall
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 58
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Book Description
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.
