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

1963 Annals of Geophysics  
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
more » ... 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.
doi:10.4401/ag-5234 doaj:abd6f591bf914185b3047d842e54e836 fatcat:3gmh6qrumfayxezie3lmagivyy