Second-Order Theory for a Thin Wing in Supersonic Flow with a Weak Spanwise Entropy Gradients PDF Download
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Author: PETER G. WILBY Publisher: ISBN: Category : Languages : en Pages : 1
Book Description
The 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: ISBN: Category : Languages : en Pages : 1
Book Description
The 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
Author: PETER G. WILBY
Author: Peter G. Wilby
Author: Peter G. Wilby
Author: 
Author: 
Author: United States. National Aeronautics and Space Administration
Author: International Council of the Aeronautical Sciences
Author: United States. Air Force. Office of Aerospace Research
Author: 
Author: United States. Air Force