Steady/unsteady aerodynamic analysis of wings at subsonic, sonic and supersonic Mach numbers using a 3D panel method
✍ Scribed by Jeonghyun Cho; Cheolheui Han; Leesang Cho; Jinsoo Cho
- Publisher
- John Wiley and Sons
- Year
- 2003
- Tongue
- English
- Weight
- 156 KB
- Volume
- 42
- Category
- Article
- ISSN
- 0271-2091
- DOI
- 10.1002/fld.577
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✦ Synopsis
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. Copyright © 2003 John Wiley & Sons, Ltd.