Author: J. C. McMullenPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 38
Book Description
Boundary Layer Transition on the NOL Standard Cone in the Ballistic Research Laboratories' Supersonic Wind Tunnels
Author: J. C. McMullenPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 38
Book Description
Boundary Layer Transition at Supersonic Speeds
Author: E. R. Van DriestPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 108
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.
Boundary-layer Transition on Cones Near Mach One in an Aeroballistic Range
Author: J. Leith PotterPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 36
Book Description
The feasibility of determining Reynolds numbers of boundary layer transition on sharp, 10-deg, semiangle cones at slightly supersonic free-stream Mach numbers, 1.04 = or
Correlations of Supersonic Boundary-layer Transition on Cones Including Effects of Large Axial Variations in Wind-tunnel Noise
Author: Fang-Jenq ChenPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 60
Book Description
Measurement of Boundary-layer Transition on a Standard Model to Determine the Relative Disturbance Level in Two Supersonic Wind Tunnels
Author: A. H. LangeA Correlation of Artifically Induced Boundary-layer Transition Data from Blunt Slender Cones at Hypersonic Speeds
Author: Albert H. BoudreauPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 18
Book Description
Boundary-layer Transition Study of Several Pointed Bodies of Revolution at Supersonic Speeds
Author: William A. CasselsPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 76
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.
Critical Evaluation of Transition from Laminar to Turbulent Shear Layers with Emphasis on Hypersonically Traveling Bodies
Author: Mark Vladimir Morkovin (|d)Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 152
Book Description
Author: 
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