Prediction of Wing-Body-Store Aerodynamics Using a Small Perturbation Method and a Grid Embedding Technique,
CANADAIR LTD MONTREAL (QUEBEC)
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A computer program providing accurate and cost effective predictions of transonic flow fields about three dimensional configurations has been developed at Canadair. The computation scheme uses the Small Perturbation Equation and a grid embedding technique. The flow field is solved iteratively, using successive line overrelaxation. The comparison between computed results and experiments for a wing body and a generic wing body pylon store configuration show that a good level of accuracy can be obtained with this approach. The program was written with the overall emphasis on lowering the computation time and is considered as a stepping stone towards a full aircraft-store aerodynamic simulation. The potential of the method for analyzing complex three dimensional configuration is discussed, showing that the code is a very practical tool for the design office, for parametric studies or as a lead program for more sophisticated investigations using Euler or Navier Stokes solvers.