Supersonic nonuniform flow over a trapezoidal profile

Gogish, L. V.; Dashevskaya, S. G.

doi:10.1007/bf01049836

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“…Therefore, a considerable attention is paid at present to the solution of the problem of active control of flow around the bodies by an energy and/or power effect on the free stream,/ in particular, by a heat supply in front of the body in supersonic flow. A considerable influence of a stepwise temperature distribution in the free stream of the aerodynamic lift force was shown in the work [12] by the example of the hypersonic gas flow of a trapezoid airfoil. For a technological realization of the technique of flow control under consideration, it is proposed to use the laser and ultra-high-frequency radiations and the electric discharge.…”

Section: Introductionmentioning

confidence: 99%

Estimation of energetic efficiency of heat supply in front of the aircraft at supersonic accelerated flight. Part 1. Mathematical models

Latypov

2008

Thermophys. Aeromech.

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Fuel economy at boost trajectory of the aerospace plane was estimated during energy supply to the free stream. Initial and final flight velocities were specified. The model of a gliding flight above cold air in an infinite isobaric thermal wake was used. The fuel consumption rates were compared at optimal trajectory. The calculations were carried out using a combined power plant consisting of ramjet and liquid-propellant engine. An exergy model was built in the first part of the paper to estimate the ramjet thrust and specific impulse. A quadratic dependence on aerodynamic lift was used to estimate the aerodynamic drag of aircraft. The energy for flow heating was obtained at the expense of an equivalent reduction of the exergy of combustion products. The dependencies were obtained for increasing the range coefficient of cruise flight for different Mach numbers. The second part of the paper presents a mathematical model for the boost interval of the aircraft flight trajectory and the computational results for the reduction of fuel consumption at the boost trajectory for a given value of the energy supplied in front of the aircraft.

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Section: Introductionmentioning

confidence: 99%

Estimation of energetic efficiency of heat supply in front of the aircraft at supersonic accelerated flight. Part 1. Mathematical models

Latypov

2008

Thermophys. Aeromech.

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Supersonic nonuniform flow over a trapezoidal profile

Cited by 1 publication

References 0 publications

Estimation of energetic efficiency of heat supply in front of the aircraft at supersonic accelerated flight. Part 1. Mathematical models

Estimation of energetic efficiency of heat supply in front of the aircraft at supersonic accelerated flight. Part 1. Mathematical models

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