Application of Transonic Inverse Method to the Development of Aerospace Products
A three-dimensional transonic wing design method which was developed by Dr. S. Takanashi(Ref.1) has been used to various aero-design fields in Mitsubishi Heavy Industries, Ltd.
The inverse code is originally based on a small perturbation equation. The present method has an iterative “residual-correction” concept combined with existing three-dimensional transonic flow analysis code. The main advantages of this approach is that the analysis code is treated as a “black box” and, as a result, it can be easily replaced by any other code. Aerodynamic designers are therefore able to adopt any flow analysis code that is considered to be appropriate for their designing purposes. The geometry is corrected iteratively according to the difference between the specified and computed pressure distribution, starting from a baseline geometry.
This paper shows two applicated examples of this inverse problem. One is for swept wing of typical civil transport. The other is for non-planar wing of H-II Orbiting Plane(HOPE) tipfin configuration.
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- Takanashi, S., “Iterative Three-Dimensional Transonic Wing Design Using Integral Equations,” Journal of Aircraft Vol. 22, No. 8, Aug. 1985.Google Scholar
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- Kaiden, T., Ogino, J. and Takanashi, S., “Non-planar Wing Design by Navier-Stokes Inverse Computation,” AIAA-92–0285, Jan. 1992.Google Scholar