Improvement of forebody/inlet integration for hypersonic vehicle

Bissinger, Norbert C.; Blagoveshchensky, N.A; Gubanov, Anatoly; Gusev, V. N.; Starukhin, V.P; Voevodenko, Nina; Zadonsky, Sergey Mikhailovich

doi:10.1016/s1270-9638(99)80009-1

Cited by 9 publications

(2 citation statements)

References 2 publications

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“…al. [6] had studied the influence of forebody shape on intake characteristics using CFD simulation for Mach numbers varying from 3 to 7. They proposed that the convex lower surfaces should be shunned for forebodies to minimize the pressure losses.…”

Section: Introductionmentioning

confidence: 99%

Experimental Evaluation of Isolated Intake for Hypersonic Air- Breathing Vehicle

Thiagarajan,

Sharma

2023

joast

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Isolated intake of an air-breathing conceptual hypersonic demonstrator vehicle has been experimentally characterized simulating the entry Mach number and the entry flow direction. A 1:8 scale intake model having provision to vary the entry area of the internal compression portion by means of actuating the intake cowl has been tested in the supersonic freestream Mach numbers 3, 3.44 and 3.9. Tests were carried out in the 0.3 m x 0.3 m trisonic wind tunnel at National Aerospace Laboratories, Bangalore. The result pertaining to M¥ = 3.44 is discussed in this paper. The effect of cowl position on the intake starting characteristics and performance are analyzed using wall pressure measurements, schlieren and oil flow visualization. Intake unstart occurred before the cowl reaching to its fully open position with the original hinge location. Essentially the strength of cowl leading edge shock increases as the cowl opening angle increases. The strong shock-boundary layer interaction in the convergent portion of intake aids the growth of the separation bubble in the flow path and that cause the intake to unstart. Improvement of intake starting by means of shifting the cowl hinge location downstream was attempted. Shifting the cowl hinge location downstream has improved the intake starting characteristics. On the improved configuration, the effect of combustion induced back pressure and the effect of cowl opening speed on intake unstart have been analyzed and quantified.

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Section: Introductionmentioning

confidence: 99%

Experimental Evaluation of Isolated Intake for Hypersonic Air- Breathing Vehicle

Thiagarajan,

Sharma

2023

joast

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“…As a result, growth of total pressure recovery can considerably improve specific impulse of an engine and consequently the fuel consumption needed for flight. The example presented in Paper [1] shows that due to appropriate shaping of the forward part of the vehicle making preliminary compression more intense, both the intake mass flow rate and pressure recovery factor could be enhanced by 30% at Mach number M ∞ = 7 at angle-of-attack range 0 ≤ α ≤ 6°as compared to the conventional shape of the nose part having the axial symmetry.…”

Section: Introductionmentioning

confidence: 99%

Theoretical fundamentals of airframe/propulsion integration for high-speed aircraft

Gubanov

2019

Adv. Aerodyn.

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Fundamental features of aerodynamic interference and integration of airframes and air-breathing jet engines for high-speed flight vehicles are studied within the framework of supersonic small perturbation theory. Both the influence of airframe components on air intakes performance and influence of intakes on vehicle external aerodynamics are under consideration. Analytical relations and specific examples show that significant favorable interference between airframes and air intakes can be realized by using preliminary compression of the flow in front of intakes at flight Mach numbers exceeding approximately 3.

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Numerical study of attack angle characteristics for integrated hypersonic vehicle

Huang

Wang

2009

Appl. Math. Mech.-Engl. Ed.

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Improvement of forebody/inlet integration for hypersonic vehicle

Cited by 9 publications

References 2 publications

Experimental Evaluation of Isolated Intake for Hypersonic Air- Breathing Vehicle

Experimental Evaluation of Isolated Intake for Hypersonic Air- Breathing Vehicle

Theoretical fundamentals of airframe/propulsion integration for high-speed aircraft

Numerical study of attack angle characteristics for integrated hypersonic vehicle

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