An Experimental and Theoretical Study of the Aerodynamic Characteristics of Some Generic Missile Concepts at Mach Numbers from 2 to 6.8 PDF Download
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Languages : en
Pages : 34
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Category :
Languages : en
Pages : 34
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Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781729090879
Category : Science
Languages : en
Pages : 34
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Book Description
A study has been made of the experimental and theoretical aerodynamic characteristics for some generic high-speed missile concepts at Mach numbers from 2 to 6.8. The basic body for this study had a length-to-diameter ratio of 10 with the forward half being a modified blunted ogive and the rear half being a cylinder. Modifications made to the basic body included the addition of an after body flare, the addition of highly swept cruciform wings and the addition of highly swept aft tails. The effects of some controls were also investigated with all-moving wing controls on the flared body and trailing-edge flap controls on the winged body. The results indicated that the addition of a flare, wings, or tails to the basic body all provided static longitudinal stability with varying amounts of increased axial force. The control arrangements were effective in producing increments of normal-force and pitching-moment at the lower Mach numbers. At the highest Mach number, the flap control on the winged body was ineffective in producing normal-force or pitching-moment but the all-moving wing control on the flared body, while losing pitch effectiveness, still provided normal-force increments. Calculated results obtained through the use of hypersonic impact theory were in generally good agreement with experiment at the higher Mach numbers but were not accurate at the lower Mach numbers. Spearman, M. Leroy and Braswell, Dorothy O. Langley Research Center RTOP 505-69-20-01...
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Category : Aeronautics
Languages : en
Pages : 956
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Category : Government publications
Languages : en
Pages : 1746
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Author:
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Category : Science
Languages : en
Pages : 552
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Author:
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Category : Aeronautics
Languages : en
Pages : 122
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 134
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Category : Aeronautics
Languages : en
Pages : 538
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Category : Aeronautics
Languages : en
Pages : 654
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Author: Kunyuan Zhang
Publisher: Springer Nature
ISBN: 9811507279
Category : Science
Languages : en
Pages : 340
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Book Description
This book presents systematic research results on curved shock wave-curved compression surface applied to the compression surface design of supersonic–hypersonic inlet, which is a brand new inlet design. The concept of supersonic inlet curved compression discussed originated from the author’s research at the Deutsches Zentrum fur Luft- und Raumfahrt (DLR SM-ES) in the early 1990s. This book introduces the research history, working characteristics, performance calculation and aerodynamic configuration design method of this compression mode in detail. It also describes method of estimating the minimum drag in inlet and drag reduction effect of curved compression and proposes a new index for evaluating unit area compression efficiency of the inlet. Further, it reviews the relevant recent research on curved compression. As such it is a valuable resource for students, researchers and scientists in the fields of hypersonic propulsion and aeronautics.
