The hypersonic merged layer flows on thin wedges with half angles of 2 and 5 degrees were analyzed by obtaining the solutions of the NAVIERSTOKES equations with the semi-implicit finitedifference technique. The calculated flow fields with M∞=20 and Rex∞ ranging from 5, 000 to 20, 000 showed that the NAVIER-STOKES equations can describe the merged layer flow qualitatively well, while the merging effect seems to appear nearer the leading edge than in actual flows.
New methods of estimating the subcritical response of a wing excited by the random turbulence of flow are presented. They are based on the fitting technique to an autoregressive model and on the solving of a polynominal equation. The feasibility of the new methods are investigated comparing them with the existing curve-fit techniques which use the randomdec signature or autocorrelation function. The results of the numerical experiments show that one of these new methods using the fitting technique of autocorrelation function to an autoregressive model is very promising in accuracy, time of computation and ease of application.