This paper deals with the nonlinear theory on the highly loaded wing of the finite span with the tip blowing. The authors have published the paper on the nonlinear theory of the ordinary three-dimensional wing without the tip blowing which will be available even in such a high circulation region as PRANDTL'S linear theory cannot be applied, and the present investigation is carried out on the basis of the previous results. It is concluded that the ratio of the lift coefficient to the physical aspect ratio will increase and that of the induced drag coefficient to the physical aspect ratio will decrease by the pertinent wing tip blowing in comparison with the case without it.
An experimental study of the chocked jet was made using axisymmetric nozzles to investigate the flow property and the acoustical characteristics. The character of the choked jet noise had been shown by many authors to be determined by that of the flow itself and, in particular, by the regular shock wave spacing. This experiment showed that the exit velocity had signigicant relation with the peak frequency of the noise generated by the flow. A new method for calculating the boundary of the choked jet is presented which is simpler than other methods, that is, the characteristics method and so all. The new method is based on the fact that the underexpanded flow is determined by the exit nozzle configuration, the exit vellocity and, above all, the static pressure of the flow at the exit. The results were compared with photographs of actual jets and other author's ones. Favorable agreement was obtained.
The present work is concerned with the steady state two-dimensional thermal stress problems in a thick circular cylinder having a rectangular hole when the both surfaces are kept at the constant temperatures. The analysis is carried out by using the complex variable approach. In performing the calculation of the parametric coefficients included in the complex stress functions we adopt the double-perturbation technique.