论文信息 - Thrust nozzle optimization including boundary-layer effects

Thrust nozzle optimization including boundary-layer effects

An optimization analysis employing the calculus of variations and a numerical relaxation scheme for applying the results are presented for the design of axisymmetric, maximumthrust nozzle contours including boundary-layer effects. The method is illustrated by comparison with a known solution without boundary-layer effects. A parametric study of boundary-layer effects for a range of parameters typical of scramjet thrust nozzles is presented.

[1] A. N. Kraiko. Variational problems of gas dynamics of nonequilibrium and equilibrium flows , 1964 .

[2] A. N. Kraiko,et al. On the construction of bodies of optimum shape in a supersonic stream , 1964 .

[3] A. N. Kraiko,et al. A variational problem of one-dimensional nonequilibrium gasdynamics , 1966 .

[4] G. Rao,et al. Spike Nozzle Contour for Optimum Thrust , 1961 .

[5] S. N. B. Murthy,et al. Optimization of Supersonic Rocket Nozzles with Viscous Flow. , 1970 .

[6] J. D. Hoffman,et al. A general method for determining optimum thrust nozzle contours for chemically reacting gas flows. , 1966 .

[7] H. Thompson,et al. Design of optimized three-dimensional nozzles. , 1966 .

[8] G. Rao. Exhaust Nozzle Contour for Optimum Thrust , 1958 .

[9] J. D. Hoffman,et al. Optimum thrust-nozzle contours for gas-particle flows. , 1967 .

[10] D. R. Bartz. Turbulent Boundary-Layer Heat Transfer from Rapidly Accelerating Flow of Rocket Combustion Gases and of Heated Air , 1965 .

[11] J. D. Hoffman,et al. A general method for determining optimum thrust nozzle contours for gas-particle flows. , 1966 .