Flight-ground conversion method of push-resistance characteristic of motorized aircraft

Abstract

The invention provides a flight-ground conversion method of the push-resistance characteristic of a motorized aircraft. A wind tunnel adopts total enthalpy h0, dynamic pressure q[indefinite] and Mach number M[indefinite] as simulation parameters. The content of oxygen in a test gas medium is maintained as same as that in pure air. A test model is an integrated aircraft motorized full size model, which means the size of a ground test model is identical to the size of an aircraft in a real flight condition. Meanwhile, the wind tunnel meets simulation rules of pneumatic and engine testing. The motor specific impulse is used as a correlation function of flight-ground conversion, and the correlation function is shown in the following formula which is described in the specification. An aircraft total thrust predicted value of the aircraft in flight is obtained using the abovementioned formula. The flight-ground conversion method of the push-resistance characteristic of the motorized aircraft provided by the invention can obtain the aircraft total thrust predicted value of the aircraft in flight and can provide data support for estimating push-resistance characteristics of an integrated aircraft.

Description

technical field [0001] The invention belongs to the technical field of aerodynamics, in particular to a space-to-earth conversion method for the thrust-drag characteristic of a powered aircraft. Background technique [0002] Existing typical air-breathing integrated aircraft fuselage and engine are highly integrated, such as figure 1 As shown, 1 is the integrated configuration of the body, the front lower surface of the fuselage is the compression surface 2 of the front body of the engine inlet, the rear lower surface of the fuselage is the rear body expansion surface 3 of the engine tail nozzle, and 4 is the fuel injection, There is no clear dividing line between the airframe and the engine. [0003] In order to study the aerodynamic and engine performance of the aircraft, it is necessary to divide the airframe / engine force interface. Using the "noseto tail" division method (Luo Jinling, Zhou Dan, Kang Honglin, et al. A review of research on experimental methods for typic...

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Problems solved by technology

[0007] At present, the research on space-ground correlation is focused on the conversion of aircraft aerodynamic data, and there is little research on the space-ground conversion of engine thrust performance of air-breathing integrated aircraft

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