Wind Tunnel Tests of Two-dimensional and Half-axisymmetric Inlet Models at Mach Numbers 1.5 Through 3.0 PDF Download
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Author: Frederick K. Hube
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 278
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Book Description
Author: Frederick K. Hube
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 278
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Book Description
Author: Frederick K. Hube
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 0
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Book Description
Author: Frederick K. Hube
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 274
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Book Description
Author: Frederick K. Hube
Publisher:
ISBN:
Category :
Languages : en
Pages : 60
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Book Description
An axisymmetric, variable geometry, two-thirds scale model of a NASA Hypersonic Research Engine (HRE) inlet was tested at Mach numbers 4, 5, 6, and 8. Surface pressures and temperatures were measured on the inlet centerbody and inside the cowl. Pitot pressure measurements were made at four stations along the internal passage. The measurements were obtained for various cowl positions at free-stream Reynolds numbers from 1.08 to 5.76 million (based on a 12-in. cowl diameter) and over an angle-of-attack range from -5 to +5 deg. The model walls were internally cooled and maintained at a minimum frost-free condition at each test condition. Selected results are presented to illustrate the effects of cowl position, angle of attack, Mach number, and Reynolds number on the surface and rake station measurements. Inlet performance data at design operating conditions are also presented. (Author).
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
An axisymmetric, variable geometry, two-thirds scale model of a NASA Hypersonic Research Engine (HRE) inlet was tested at Mach numbers 4, 5, 6, and 8. Surface pressures and temperatures were measured on the inlet centerbody and inside the cowl. Pitot pressure measurements were made at four stations along the internal passage. The measurements were obtained for various cowl positions at free-stream Reynolds numbers from 1.08 to 5.76 million (based on a 12-in. cowl diameter) and over an angle-of-attack range from -5 to +5 deg. The model walls were internally cooled and maintained at a minimum frost-free condition at each test condition. Selected results are presented to illustrate the effects of cowl position, angle of attack, Mach number, and Reynolds number on the surface and rake station measurements. Inlet performance data at design operating conditions are also presented. (Author).
Author: United States. National Aeronautics and Space Administration Scientific and Technical Information Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 478
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 896
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Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author:
Publisher:
ISBN:
Category : Industrial hygiene
Languages : en
Pages : 854
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Author: John R. Spreiter
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 44
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Summary: The degree to which experimental results obtained under choking conditions in a wind tunnel with solid walls simulate those associated with an unbounded flow with free-stream Mach number 1 is investigated for the cases of two-dimensional and axisymmetric flows. It is found that a close resemblance does indeed exist in the vicinity of the body, and that the results obtained in this way are generally at least as accurate as those obtained in a transonic wind tunnel with partly open test section. Some of the results indicate, however, that substantial interference effects, particularly those of the wave reflection type, may be encountered under certain conditions, both in choked wind tunnels and in transonic wind tunnels, and that the reduction of these interference effects to acceptable limits may require the use of models of unusually small size.
Author: United States. National Aeronautics and Space Administration. Scientific and Technical Information Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 470
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