| Abstract: | ![]()
The existing methods of constructing an “ideal” contour (i.e., a contour without taking account of viscosity) for aerodynamic nozzles has a number of drawbacks: they are extremely unwieldly and are not versatile and, moreover, they give in practice an impairment of the flow uniformity, caused by nonconformity of the true flow in the transonic region assumed in the solution, as only the hypersonic flow region is usually calculated. In this paper, a method is proposed for calculating the ideal contours of aerodynamic nozzles with transition through the velocity of sound, which is free from these drawbacks. Cauchy's problem is solved numerically by the method in [1]. A specially corrected pressure distribution, obtained experimentally [2], is used as the initial distribution. Examples of the calculation are given for the ideal contours of plane, axisymmetrical and annular aerodynamic nozzles. |
