In this report, the gust responses of a three dimensional wing are investigated theoretically and experimentally i.e. the responses to the sinusoidal gust and the random gust are obtained theoretically and the both are compared with the experimental results respectively. The responses to the sinusoidal gust are calculated by the method of lifting-line theory and the response functions are obtained for the wing of various aspect ratio. These results are compared to the experimental values which were obtained by the wind tunnel experiments for the wing of aspect ratio of 3.16. As the results, it is found that the both agree well with each other. For the responses to the random gust, the power spectral density functions and the frequency transfer functions of the lift force of a wing are calculated with the method of lifting-line theory. In this case, it is considered that the gust varies along the wing span i.e. the reduced frequency along the wing span, k2, is introduced. Therefore, the frequency transfer functions have two variables and these results are compared with the experimental values and the both agree well with each other.
This paper is an extension of the previous paper5), and analyzes the inviscid hypersonic vibrational nonequilibrium flow in the shock layer about the stagnation region of a blunt body generating a spherical shock wave. With the assumptions of thin shock layer, strong shock and constant relaxation time, expressions for the temperature, internal energy and density are derived. These expressions have been evaluated for a sphere for various shock radius, ranging from near equilibrium to near frozen flow. Comparison of the calculated temperature distribution with those based upon a numerical solution shows reasonable agreement in near equilibrium flow.