Second-order Theory for a Thin Wing in Supersonic Flow with a Weak Spanwise Entropy Gradient
Author: Peter G. Wilby
Publisher:
Published: 1961
Total Pages: 20
ISBN-13:
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Author: Peter G. Wilby
Publisher:
Published: 1961
Total Pages: 20
ISBN-13:
DOWNLOAD EBOOKAuthor: PETER G. WILBY
Publisher:
Published: 1961
Total Pages: 1
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DOWNLOAD EBOOKThe three-dimensional perturbation velocities over an infinite thin wing with a sharp leading edge in non-uniform supersonic flow are derived and used to investigate the second-order contribution to the pressure coefficient on a wing surface, due to a spanwise entropy gradient. Pressure distributions are calculated for a wedge section wing at various Mach numbers for probable values of entropy gradient. Results show that entropy gradient effects can be important. Procedure for application of the theory is given for the case of a wing situated behind the curved shock generated by a blunt nosed body. (Author).
Author: Peter G. Wilby
Publisher:
Published: 1961
Total Pages:
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Publisher:
Published: 1962
Total Pages: 1116
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Publisher:
Published: 1962
Total Pages: 230
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DOWNLOAD EBOOKAuthor: United States. National Aeronautics and Space Administration
Publisher:
Published: 1962
Total Pages: 1556
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DOWNLOAD EBOOKAuthor: International Council of the Aeronautical Sciences
Publisher:
Published: 1964
Total Pages: 1216
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DOWNLOAD EBOOKAuthor: United States. Air Force. Office of Aerospace Research
Publisher:
Published: 1959
Total Pages: 800
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DOWNLOAD EBOOKAuthor: United States. Air Force
Publisher:
Published: 1962
Total Pages: 520
ISBN-13:
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