1. Asecond wing geometry, the Wing-C configuration of Xinson and Burdgasl*, was used to verify the analysis code far twisted wings. Wing C is a fighter type wing with a low aspect ratio (AB * 2.8), high leading edge 'sweep and taper ( A * 45', TR - 0.3), and 8' of twist f r w root to tip. The computed pressure coefficients at four span stations are compared vith the experimental data given in Reference 14 for the Wing C design case (n, 0.85, 0 - 5.9") and vich WING results in Fig. 4. The same Mach number'and angle of attack corrections used in Ref. 2 (AH I - 0.02, Ad I -0.9) were used in this test case. n e agreement with both the experimental data and the TWING results is quite good for all scationr except the t i p where viscous effects are most prominent.
2. in the direct region of the potential flov critical and supercritical Mach numbers using a w solver. 72x17110 grid, only the supercritical results for
3. This research was performed through sponsorship of the Daved Y. Taylor Naval Ship Research and Development Center under Nevy Contract i?00157-81-C-0078. The authors wish to thank J. C. Sourh and J. D. Keller at NASA Langley for providing somputer time and software.