A method for obtaining thermal aerodynamic performance of a flying vehicle

Abstract

The invention provides a method for obtaining thermal aerodynamic performance of a flying aircraft. Based on the idea of interface division, the whole flying aircraft interface is divided into an engine interface and an aerodynamic interface, cold aerodynamic performance data of the flying aircraft are superimposed on cold and thermal state difference of the engine interface and cold and thermal state difference of the pneumatic interface as thermal state aerodynamic performance of the flying aircraft, and a problem that thermal performance is difficult to obtain at present is solved in the prior art. The method is advantaged in that data accuracy is guaranteed by wind tunnel test data as a baseline, moreover, cold and thermal state difference of the engine interface and cold and thermal state difference of the pneumatic interface instead of the absolute amount are obtained through CFD calculation, systematic deviation between CFD calculation and the test is avoided, and data accuracyis guaranteed.

Description

technical field [0001] The invention belongs to the field of engine testing, and in particular relates to a method for acquiring thermal performance of an engine flight test aircraft. Background technique [0002] In recent decades, combined power technologies that can greatly expand the flight speed range / airspace envelope of aircraft have begun to develop rapidly. At the current stage, most combined power engines such as RBCC and TBCC are still in the ground principle prototype verification, and a small number of engine flight tests. The flying test refers to relying on the rocket power of the flying vehicle to complete the predetermined flight profile, provide real flight conditions for the combined engine to be tested, and verify the key technologies of the combined engine during the flight. During the flying flight, the combined engine is always in the working state, and the hot jet flow after the engine combustion has a severe impact on the aerodynamic performance of ...

AI Technical Summary

Problems solved by technology

CFD numerical calculation can theoretically obtain the thermal aerodynamic performance, but it is necessary to simulate the combustion chemical reaction of the internal flow and the flow field of the entire aircraft. The calculation of the profile state is huge, and the simulation accuracy of the complex combustion process is not high

At present, there is no reliable and simple method to obtain the thermal performance of the flying vehicle

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