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In the immediate postwar period, he studied the use of a biconvex wing profile for high-speed aircraft and developed the Schlieren Flow Visualization method of predicting the impact of shock waves on aircraft wings.
Compression is achieved through the ram-air effect in an intake similar to that found on a high-speed aircraft like Concorde, where intake ramps create shock waves that compress the air.
Initially he worked in the field of missile aerodynamics and later shifted to CFD and devised the Roe solver for numerical computation of compressible flows with shocks.
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He has developed approximate Riemann solver called Roe solver for compressible flows with shocks.