Author: Donald M. Kuehn
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 48
Book Description
Experimental Investigation of the Pressure Rise Required for the Incipient Separation of Turbulent Boundary Layers in Two-dimensional Supersonic Flow
Author: Donald M. Kuehn
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 48
Book Description
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 48
Book Description
Experimental Investigation of Pressure Rise Required for Incipient Separation of Turbulent Boundary Layers in 2-dimensional Supersonic Flow [with List of References]
NASA Technical Memorandum
Investigation of a Mixed-compression Axisymmetric Inlet System at Mach Numbers 0.6 to 3.5
Author: Donald B. Smeltzer
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 252
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 252
Book Description
Space Programs Summary
Author: Jet Propulsion Laboratory (U.S.)
Publisher:
ISBN:
Category : Space flight
Languages : en
Pages : 372
Book Description
Publisher:
ISBN:
Category : Space flight
Languages : en
Pages : 372
Book Description
NASA Technical Note
Semiannual Report to the Congress
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 920
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 920
Book Description
Reports and Documents
Author: United States. Congress
Publisher:
ISBN:
Category :
Languages : en
Pages : 1564
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 1564
Book Description
Inhibition of Flow Separation at High Speed
Author: Jack Norman Nielsen
Publisher:
ISBN:
Category : Correlation (Statistics)
Languages : en
Pages : 68
Book Description
The report describes the results of a wind-tunnel test program on an ogive-cylinder-flare combination to determine the extent of laminar separation as a function of wall temperature for fixed free-stream Reynolds number per unit length at a free-stream Mach number of 8.0. The objective of the tests was to see if separation could be eliminated entirely by cooling the wall to a sufficiently low value. Pressure and temperature distributions spanning the separation region were made on a quick-insertion model, but the location of the separation point could not be obtained during the tests. Accordingly, a combined experimental-theoretical method was developed for determining the separation point location. Correlation of the separation length with model temperature ratio indicated that the separation distance was small and was rapidly approaching zero at the lowest wall temperature ratio achieved experimentally. The apparent critical wall temperature ratio so indicated by the data was lower than the theoretical ratio. It was not possible to achieve sufficiently low temperatures to see if separation could be entirely eliminated. Possible reasons for the difference between experiment and theory are discussed.
Publisher:
ISBN:
Category : Correlation (Statistics)
Languages : en
Pages : 68
Book Description
The report describes the results of a wind-tunnel test program on an ogive-cylinder-flare combination to determine the extent of laminar separation as a function of wall temperature for fixed free-stream Reynolds number per unit length at a free-stream Mach number of 8.0. The objective of the tests was to see if separation could be eliminated entirely by cooling the wall to a sufficiently low value. Pressure and temperature distributions spanning the separation region were made on a quick-insertion model, but the location of the separation point could not be obtained during the tests. Accordingly, a combined experimental-theoretical method was developed for determining the separation point location. Correlation of the separation length with model temperature ratio indicated that the separation distance was small and was rapidly approaching zero at the lowest wall temperature ratio achieved experimentally. The apparent critical wall temperature ratio so indicated by the data was lower than the theoretical ratio. It was not possible to achieve sufficiently low temperatures to see if separation could be entirely eliminated. Possible reasons for the difference between experiment and theory are discussed.
Experimental Separation Studies for Two-dimensional Wedges and Curved Surfaces at Mach Numbers of 4.8 to 6.2
Author: James R. Sterrett
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 56
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 56
Book Description