Thin cylindrical wing streamlined by supersonic gas flow

Problem of stationary longitudinal streamlining thin cylinder-shaped wing by supersonic flow of non-viscous compressible gas under small attack angle, is analysed. Differential hyperbolic equation describing such flow within the framework of linearised theory conditions, is transformed into the wave equation whose solution is found using Volterra formula. Disturbance velocity potentials, pressure factors on the internal and external surfaces of cylindrical shell, are determined.