Evaluation of the aerothermodynamic field produced by a pseudospheric body of mercury type at M = 22.6 flying in air in thermodynamic equilibrium

Abstract

Tlie differential equations valid after tlie shock are first<br />given in curvilinear coordinates; the cbosen unknowns are the two velocity<br />components and the entropy and enthalpy. A function of entropy and<br />enthalpy is then determined, by ineans of wliich ali the thermodynamic<br />variables of the fluir are " coherently " approximated. Later on, the density<br />and ali the otlier kinematic and thermodynamic variables are calculated<br />immediately after the shock, taking the angle a as a parameter. The shape<br />of the body is now taken into account and a convenient shape of the shock<br />wave is given.<br />The differential equations are then integrated with a step-by-step<br />procedure, until the stagnation entropy is reached 011 the body.<br />Finally the pressure and the temperature on the body are given. A<br />sonic-to-stagnation pressure of 0.0 is the result, instead of 0.523 for a perfect<br />gas.