Supersonic non-uniform incoming flow maximum thrust nozzle and its wall surface determination method

Abstract

The invention provides a supersonic non-uniform inflow maximum-thrust nozzle and a wall determination method therefor. The wall determination method for the supersonic non-uniform inflow maximum-thrust nozzle includes the steps of S1, determining an initial boundary of the supersonic non-uniform inflow maximum-thrust nozzle according to non-uniform inflow parameter; S2, determining a core area of the supersonic non-uniform inflow maximum-thrust nozzle according to the initial boundary by a method of characteristics; S3, performing iterative solution in the core area to determine wall profile of the supersonic non-uniform inflow maximum-thrust nozzle according to the principle of conservation of mass and the method of characteristics; and S4, determining the wall of the supersonic non-uniform inflow maximum-thrust nozzle according to the wall profile of the supersonic non-uniform inflow maximum-thrust nozzle. The supersonic non-uniform inflow maximum-thrust nozzle and the wall determination method therefor have the advantage that the maximum-thrust nozzle applicable to supersonic non-uniform inflows can be produced.

Description

technical field

[0001] The invention relates to the field of aerodynamic design, more specifically, to a supersonic non-uniform incoming flow maximum thrust nozzle and a method for determining its wall surface. Background technique

[0002] For hypersonic vehicles using scramjet engines, the ramjet resistance of scramjet engines is very large, and the ratio of total thrust to net thrust increases from 1 to 10 for traditional air-breathing engines. The exhaust nozzle is the main part of the engine to generate thrust. When the flight Mach number is 6.0, the thrust generated by it can account for about 70% of the total thrust of the engine. It is not difficult to see that the design of the exhaust nozzle will vary. directly affects the performance of the entire engine. The paper "ExhaustNozzleContourforOptimumThrust" (G.V.R.Rao, JetPropulsion, Vol.28, No.6June1958) proposed a maximum thrust nozzle design method based on uniform incoming flow. The design process of this method ...

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