Tlie differential equations valid after tlie shock are firstgiven in curvilinear coordinates; the cbosen unknowns are the two velocitycomponents and the entropy and enthalpy. A function of entropy andenthalpy is then determined, by ineans of wliich ali the thermodynamicvariables of the fluir are " coherently " approximated. Later on, the densityand ali the otlier kinematic and thermodynamic variables are calculatedimmediately after the shock, taking the angle a as a parameter. The shapeof the

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... dy is now taken into account and a convenient shape of the shockwave is given.The differential equations are then integrated with a step-by-stepprocedure, until the stagnation entropy is reached 011 the body.Finally the pressure and the temperature on the body are given. Asonic-to-stagnation pressure of 0.0 is the result, instead of 0.523 for a perfectgas.