Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722218584
Category :
Languages : en
Pages : 24
Book Description
The flow field near four small-scale ducted-nacelle bodies of revolution has been analytically and experimentally studied to determine exterior and interior mass-flow characteristics, and to measure flow-field overpressures generated by the nacelle's forebody shape. Four nacelle models with the same profile, but of different sizes, were used in the study. Shadowgraph pictures showed inlet shocks attached to the cowl lip (indicating unchoked flow) on all four models, at all the test Mach numbers, through an angle of attack range of 0.0 to 6.0 degrees. Pressure signatures measured in the flow field of the largest of the four nacelle models were compared with those predicted by corrected and uncorrected Whitham theory. At separation distances greater than 3.0 to 4.0 inlet diameters, good agreement was found. Poorer agreement was found at extreme near-field separation distances, but this was attributed to pressure-gage limitations and probe-flow field interactions. The overall favorable results supported a conclusion that corrected Whitham theory was sufficiently accurate to make the nacelle-wing interference-lift code useful for sonic-boom analysis and the preliminary design of supersonic-cruise conceptual aircraft. Mack, Robert J. Langley Research Center RTOP 537-07-21-21...
Experimental and Theoretical Study of Flow Fields Around Ducted-Nacelle Models
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722218584
Category :
Languages : en
Pages : 24
Book Description
The flow field near four small-scale ducted-nacelle bodies of revolution has been analytically and experimentally studied to determine exterior and interior mass-flow characteristics, and to measure flow-field overpressures generated by the nacelle's forebody shape. Four nacelle models with the same profile, but of different sizes, were used in the study. Shadowgraph pictures showed inlet shocks attached to the cowl lip (indicating unchoked flow) on all four models, at all the test Mach numbers, through an angle of attack range of 0.0 to 6.0 degrees. Pressure signatures measured in the flow field of the largest of the four nacelle models were compared with those predicted by corrected and uncorrected Whitham theory. At separation distances greater than 3.0 to 4.0 inlet diameters, good agreement was found. Poorer agreement was found at extreme near-field separation distances, but this was attributed to pressure-gage limitations and probe-flow field interactions. The overall favorable results supported a conclusion that corrected Whitham theory was sufficiently accurate to make the nacelle-wing interference-lift code useful for sonic-boom analysis and the preliminary design of supersonic-cruise conceptual aircraft. Mack, Robert J. Langley Research Center RTOP 537-07-21-21...
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722218584
Category :
Languages : en
Pages : 24
Book Description
The flow field near four small-scale ducted-nacelle bodies of revolution has been analytically and experimentally studied to determine exterior and interior mass-flow characteristics, and to measure flow-field overpressures generated by the nacelle's forebody shape. Four nacelle models with the same profile, but of different sizes, were used in the study. Shadowgraph pictures showed inlet shocks attached to the cowl lip (indicating unchoked flow) on all four models, at all the test Mach numbers, through an angle of attack range of 0.0 to 6.0 degrees. Pressure signatures measured in the flow field of the largest of the four nacelle models were compared with those predicted by corrected and uncorrected Whitham theory. At separation distances greater than 3.0 to 4.0 inlet diameters, good agreement was found. Poorer agreement was found at extreme near-field separation distances, but this was attributed to pressure-gage limitations and probe-flow field interactions. The overall favorable results supported a conclusion that corrected Whitham theory was sufficiently accurate to make the nacelle-wing interference-lift code useful for sonic-boom analysis and the preliminary design of supersonic-cruise conceptual aircraft. Mack, Robert J. Langley Research Center RTOP 537-07-21-21...
Experimental and Theoretical Study of Flow Fields Around Ducted-nacelle Models
Author: Robert J. Mack
Publisher:
ISBN:
Category :
Languages : en
Pages : 20
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 20
Book Description
Experimental and Theoretical Study of Flow Fields Around Ducted-Nacelle Models
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 28
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 28
Book Description
EXPERIMENTAL AND THEORETICAL STUDY OF FLOW FIELDS AROUND DUCTED-NACELLE MODELS... NASA/TM-1998-207683... AUG. 6, 1998
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Monthly Catalog of United States Government Publications
Author:
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Category : Government publications
Languages : en
Pages :
Book Description
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages :
Book Description
Scientific and Technical Aerospace Reports
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 702
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 702
Book Description
NASA Technical Paper
Author:
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ISBN:
Category : Science
Languages : en
Pages : 210
Book Description
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 210
Book Description
NASA Scientific and Technical Publications
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 410
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 410
Book Description
NASA Langley Scientific and Technical Information Output: 1998
Author:
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Category :
Languages : en
Pages : 166
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 166
Book Description
An Improved Method for Calculating Supersonic Pressure Fields about Bodies of Revolution
Author: Robert J. Mack
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 44
Book Description
Development of near-field method for determining supersonic flow properties about bodies of revolution.
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 44
Book Description
Development of near-field method for determining supersonic flow properties about bodies of revolution.