Some Methods of Evaluating Imperfect Gas Effects in Aerodynamic Problems

Simple numerical and graphmal procedures are described for the calculation of the imperfect gas effects on the properties of steady and unsteady one-32.msnsions.l isentropic flows, the Prandtl-Meyer expansion round a corner and normal end oblique shock waves. The fun&mental equatmns of each type of flow have been put into a form in which they may be solve2 usmi: the published tables of the equilibrium properties of gases. Both thermal Land caloric imperfections have been t&en into account but relaxation time effects have been neglected. Numerical examples are given for each type of flow although the main emphasis has been plaaed on the methods rather than on the results. These basic methods have been used to calculate the magnitude of the imperfect gas effects on a number of specific aerd.ynsn3.c problems which have been ccnsidered in detail. Ncszle of hypersonic impulse tunnel Reflection of normal shook wave from rigid wall 3.5 Two-dmensionel supersonic intake List of Symbols References LIST OF I.LLUSTR.4TIONS Steady one-dimensional isentrcpic expansien Steady one-dlmensionsl isentropic expansion Prnndtl-Meyer expCansion round corner Propagatzon of one-dimensional isentropio wave (unsteady expansion) Normal shock wares Oblique shook waves Oblique shock waves Imperfect gas effects w shock tube performance Shock tube performance L5ft of flat plate Nozzle of hmerscnic impulse tunnel Reflection cf normal shock wave from rigid wall Two-dimensional supersonic intake 14 15 15 :z