On The Flow Over A Cone-cylinder Body At Mach Number One
Item
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Title
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On The Flow Over A Cone-cylinder Body At Mach Number One
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Date
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1952
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Index Abstract
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Coming Soon
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Photo Quality
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Undetermined
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Report Number
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WADC TR 52-295
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Corporate Author
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Aircraft Laboratory, Wright Air Development Center
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Extent
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33
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NTRL Accession Number
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AD003244
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Identifier
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AD0003244
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AD Number
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3244
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Access Rights
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Unknown
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Distribution Classification
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1
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DTIC Record Exists
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Yes
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Distribution Change Authority Correspondence
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AFAL ltr
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Distribution Change Action Date
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11/7/2002
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Abstract
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The flow over a cone-cylinder body at Mach number one and zero angle of attack is computed by a niimerical method in which the subsonic region is coriputed by the relaxation method while the supersonic region is constructed by the niethod of characteristics. The sonic line is then determined by an iterative process. The results indicate that transonic similarity law proposed by von Karman and Oswatitsch and Berndt based upon slender body theory can be extended to cover cone-cylinder bodies of practical slenderness ratios.
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Report Availability
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Not available via Contrails
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Date Issued
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1952-01
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Index In
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DTIC
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Type
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report
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Creator
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Yoshihara, Hideo