Tables of Supersonic Flow Around Cones of Large Yaw PDF Download
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Author: Massachusetts Institute of Technology. Department of Electrical Engineering. Center of Analysis
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 154
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Book Description
Author: Massachusetts Institute of Technology. Department of Electrical Engineering. Center of Analysis
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 154
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Book Description
Author: Joseph L. Sims
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 440
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Book Description
Author: Joseph L. Sims
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 428
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Book Description
Author: Joseph L. Sims
Publisher:
ISBN:
Category : Aerodymanics, Supersonic
Languages : en
Pages : 432
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1216
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 730
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Book Description
Author: John O. Reller
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 64
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Book Description
Abstract: Temperature recovery factors were determined for a slender, thin-walled cone-cylinder, having a 12° vertex angle and a 1.25-inch-diameter cylinder, at Mach numbers from 3.02 to 6.30. The angle-of-attack range was 0° to 45° at Mach numbers up to 3.50, and about 0° to 20° at Mach numbers from 4.23 to 6.30. A transverse cylinder of the same diameter was also tested at Mach number 3.02. Free-stream Reynolds numbers varied from 1.8 to 11.0 million per foot. Flow visualization studies of boundary-layer transition and flow separation were made and the results correlated with recovery-factor measurements.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 372
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Book Description
Author: Harry W. Carlson
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 78
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Book Description
Author: Richard R. Heldenfels
Publisher:
ISBN:
Category : Box beams
Languages : en
Pages : 712
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Book Description
A method is presented for the approximate calculation of the stresses and distortions in a box beam representing the main structural component of a swept wing with a carry-through section and with bulkheads perpendicular to the spars. The application of the method is illustrated by a numerical example and its results are compared with previously published test data.
