Linearization of solutions in supersonic flow
(In uniplanar flow, explicit formulae for potential and stream functions can be derived for both irrotational M and some irrotational W flows. We have not ascertained whether these formulae represent more than the well-known elementary radial and vortex flows.) If W = Vcpw, then Vpt = 0, a case discussed by Vazsonyi4 in the less appropriate V language. Flows with constant stagnation pressure but variable entropy and stagnation temperature from one streamline to another may be of immediate practical interest. For example the effect of variable chamber gas temperature upon thrust coefficient of a rocket with "perfect" nozzle can be computed. This calculation is possible because irrotational V flow is the special case of irrotational W flow which occurs when not only pt but also 5 and therefore Tt are constant throughout the flow (v5 = vr, = 0 is implied by V = Vipr). Accordingly the same partial differential equation (derived from the continuity equation (1.10)) is satisfied by both