Performance of a forward swept wing fighter utilizing thrust vectoring and reversing

Miller, Eugene H.

doi:10.2514/3.45268

Cited by 5 publications

References 4 publications

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Computational investigation of both geometric and fluidic compressible turbulent thrust vectoring, using a Coanda based nozzle

Nayebi,

Taeibi Rahni

2024

Physics of Fluids

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This study addresses the challenge of enhancing aircraft maneuverability, particularly for vertical landing and takeoff, focusing on the fluidic aerial Coanda high efficiency orienting jet nozzle that employs the Coanda effect to achieve thrust vectoring. This research advances understanding of the interplay between geometric and fluidic factors in thrust vectoring. Stationary, turbulent, and compressible flow conditions are assumed, employing Favre-averaged Reynolds-averaged Navier–Stokes approach with the standard k-ε model. Computational solutions were obtained using a pressure-based finite volume method and a structured computational grid. The key findings include thrust vectoring enhancement due to an increase in the total mass flow rate, septum position (at no shock wave-related issues), and Reynolds number. In addition, shock wave formation (at specific mass flow rates and septum positions) considerably affects thrust vectoring. These insights are crucial for optimizing Coanda-based nozzle design in advanced propulsion systems, including in unmanned aircraft vehicles.

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Computational investigation of both geometric and fluidic compressible turbulent thrust vectoring, using a Coanda based nozzle

Nayebi,

Taeibi Rahni

2024

Physics of Fluids

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A Semi-Empirical Approach to Aircraft Aft-End Design

Miller¹,

Delancy²,

Tamplin³

1994

International Journal of Turbo and Jet Engines

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Today's modem fighter design, with multifimction nozzles, places an increased emphasis on nozzle/airframe integration. The tools currently available to the aircraft designer for aft-end design and evaluation are model test reports, being disseminated mainly by government laboratories, and three-dimensional numerical computation codes. Test data utilization usually is limited by the suitability of the area that has been tested. The second approach, analysis, usually requires timeconsuming three-dimensional configuration data input. Recognizing the need for a quicker means of solution, useful in a preliminary design environment, a semi-empirical computer methodology has been developed for determining threedimensional aircraft afterbody performance. The essence of the approach is to construct equivalent bodies of revolution of three-dimensional bodies and then to utilize a straight or hybrid axisymmetric analysis. This approach was developed for single-and twin-engine axi symmetric and two-dimensional afterbodies. The computer code covers the Mach number range of 0 to 3.5, and includes boundary layer flow and plume entrainment calculations. The methodology was verified by comparing afterbody drag and axial and longitudinal pressure distributions. The isolated drag coefficients are then modified to account for three-dimensional afterbody flow field effects and also for aircraft component effects such as empennage, booms, interfairings, base areas, and spacing. NomenclatureS/D spacing ratio (spacing between engine/nozzle dia. at customer AR aspect ratio, area ratio connect) A/B afterburner Τ temperature ATS air-to-surface T/C thickness to chord ratio CD drag coefficient V

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Methodology for analysis of afterbodies for three-dimensional aircraft configurations

Miller¹

1988

Journal of Aircraft

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Today's modern fighter design, with multifunction nozzles, is placing an increased emphasis on nozzle/airframe integration. The current tools available to the aircraft designer for aft-end design and evaluation are model test reports, being disseminated mainly by government laboratories, and three-dimensional numerical computation codes. Test data utilization usually is limited by the suitability of the area that has been tested. The second approach, analysis, usually requires time-consuming three-dimensional configuration data input. Recognizing the need for a quicker means of solution, useful in a preliminary design environment, a semiempirical computer methodology for determining three-dimensional aircraft afterbody performance has been developed. The essence of the approach is to construct equivalent bodies of revolution of three-dimensional bodies and then to utilize a straight or hybrid axisymmetric analysis. This approach has been developed for single-and twin-engine axisymmetric and two-dimensional afterbodies. The methodology has been verified by comparisons of afterbody drag and axial and longitudinal pressure distributions. Nomenclaturelength M = Mach number MB = metric break P = pressure R = radius V = velocity W = width X = length 8 = boundary-layer height 0 = momentum thickness /A = viscosity p = density Subscripts n = nozzle s = static

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Performance of a forward swept wing fighter utilizing thrust vectoring and reversing

Cited by 5 publications

References 4 publications

Computational investigation of both geometric and fluidic compressible turbulent thrust vectoring, using a Coanda based nozzle

Computational investigation of both geometric and fluidic compressible turbulent thrust vectoring, using a Coanda based nozzle

A Semi-Empirical Approach to Aircraft Aft-End Design

Methodology for analysis of afterbodies for three-dimensional aircraft configurations

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