Record number :
92406
Title of article :
Steady/unsteady aerodynamic analysis of wings at subsonic, sonic and supersonic Mach numbers using a 3D panel method
Author/Authors :
Cho، Jeonghyun نويسنده , , Han، Cheolheui نويسنده , , Cho، Leesang نويسنده , , Cho، Jinsoo نويسنده ,
Issue Information :
روزنامه با شماره پیاپی سال 2003
Pages :
-1072
From page :
1073
To page :
0
Abstract :
This paper treats the kernel function of an integral equation that relates a known or prescribed upwash distribution to an unknown lift distribution for a finite wing. The pressure kernel functions of the singular integral equation are summarized for all speed range in the Laplace transform domain. The sonic kernel function has been reduced to a form, which can be conveniently evaluated as a finite limit from both the subsonic and supersonic sides when the Mach number tends to one. Several examples are solved including rectangular wings, swept wings, a supersonic transport wing and a harmonically oscillating wing. Present results are given with other numerical data, showing continuous results through the unit Mach number. Computed results are in good agreement with other numerical results.
Keywords :
Prandtl-Glauert factor , sonic , Ackeret factor , kernel function , frequency-domain panel method , continuity
Journal title :
INTERNATIONAL JOURNAL FOR NUMERICAL METHODS IN FLUIDS
Journal title :
INTERNATIONAL JOURNAL FOR NUMERICAL METHODS IN FLUIDS
Serial Year :
2003
Link To Document :
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