In this report the investigation on the response of a two-dimensional rigid wing to the gusts is made. The kinds of the gusts which are treated here, are that vary sinusoidally and vary randomly. The experiments are performed using a wing model which has the cross section of NACA-0012. In the case of the sinusoidal gust, the following results are obtained. (1) The results of this experiments coincide with the results of oscillating wing. (2) The values of the non-dimensional lift are lower than the value of Sears' gust function. In the case of the random gust, the frequency transfer functions of the lift show the different inclination from Sears' function. It is considered at the theoretical analysis that the thickness effect of the wing to the gust response is investigated by the numerical calculations for the sinusoidal gusts, and for the random gusts the frequency transfer functions are obtained by means of obtaining the power-spectral functions of circulation. The former affects little at the range of the experiments, but the latter coincides to the results of the experiments.
The present paper deals with a calculation method of the value of the jet momentum required to control the separation position of the twodimensional incompressible air flow with the turbulent boundary layer along the wing (or body) surface by a tangential air jet discharged from a slit equipped on it. And moreover, the effects of Reynolds number and the ratio of the slit width to the wing (or body) chord as well as those of the profile and incidence of the wing (or body), the attached distance of the external flow and the slit position, on the required jet momentum are discussed.
This paper presents theoretical and experimental results for estimating electromagnetic wave attenuations caused by the presence of rocket exhaust plumes with afterburning in the propaga- tion medium between a ground station and a rocket-powered vehicle. The approximate distributions of the velocity, temperature and concentration of the rocketplume are obtained in the analytical forms by solving the boundary layer equations under some assumptions. The distributions of the rocket composite propellant are presented in graphical form. Wave propagation characteristics passing through a flame with the high collision frequency compared to the frequency used for flame diagnostics are discussed. The predicted and experimental wave attenuations along the nozzle center axis are compared with qualitatively good agseement.