Computation of 3-D transonic flows for wings and wing-body configurations

The transonic full potential code using' body fitted coordinates with ADI/AF2 scheme is under development . The, code was evaluated for the test case of RAE WING A (Wing alone case) for three conditions, namely (1) Mach number =0 .8, and zero incidence, (2) Mach number =0 .8 ) incidence of 2 xB0;, and (3) Mach number =0 .9 and incidence 18 . Comparison with results of an available code is given . The present results show the same trend of pressure distribution as observed in experiments and' calculation for the wing-body case . The work on applying the present code to wing-- body case is in progress .13; Also, the time taken for a typical run has been considerably reduced to the order of 1 hour of CPU on NAL computer