Accession Number : AD0467593


Title :   THE EFFECT OF LONGITUDINAL VISCOSITY ON THE FLOW AT A NOZZLE THROAT.


Descriptive Note : Technical rept.,


Corporate Author : MICHIGAN UNIV ANN ARBOR AIRCRAFT PROPULSION LAB


Personal Author(s) : Sichel,Martin


Report Date : JUN 1965


Pagination or Media Count : 55


Abstract : An inviscid transonic theory appears to be inadequate to describe the flow near the throat of a converging-diverging nozzle during the transition from the symmetrical Taylor (1930) type of flow to the subsonic-supersonic Meyer (1908) flow. A viscous-transonic equation taking account of heat conduction and longitudinal viscosity has been developed previously. An exact nozzle type of similarity solution of the viscous-transonic equation, similar to the inviscid solution of Tomotika and Tamada (1950), has been found. This solution does provide a description of the gradual transition from the Taylor to the Meyer flow and shows the initial stages in the development of a shock wave downstream of the nozzle throat. The solution provides a viscous shock like transition from an inviscid supersonic accelerating flow to an inviscid subsonic decelerating flow. (Author)


Descriptors :   (*NOZZLE GAS FLOW, VISCOSITY), HEAT TRANSFER, CONVERGENT DIVERGENT NOZZLES, TRANSONIC NOZZLES, SHOCK WAVES, TRANSONIC FLOW, PARTIAL DIFFERENTIAL EQUATIONS


Distribution Statement : APPROVED FOR PUBLIC RELEASE