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).
Second-Order Theory for a Thin Wing in Supersonic Flow with a Weak Spanwise Entropy Gradients
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).
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).
Second-order Theory for a Thin Wing in Supersonic Flow with a Weak Spanwise Entropy Gradient
Second-order Theory for a Thin Wing in Supersonic Flow with a Weak Spanwise Entropy Grandient
Applied Mechanics Reviews
U.S. Government Research Reports
Advances in Aeronautical Sciences
Author: International Council of the Aeronautical Sciences
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1216
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1216
Book Description
Technical Publications Announcements with Indexes
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1556
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1556
Book Description
Proceedings
OAR Quarterly Index of Current Research Results
Author: United States. Air Force. Office of Aerospace Research
Publisher:
ISBN:
Category : Aeronautics, Military
Languages : en
Pages : 800
Book Description
Publisher:
ISBN:
Category : Aeronautics, Military
Languages : en
Pages : 800
Book Description
Index of Research Results
Author: United States. Air Force
Publisher:
ISBN:
Category :
Languages : en
Pages : 520
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 520
Book Description