Nozzle Design and Integration in an Advanced Supersonic Fighter

Miller, Eugene H.; Protopapas, J.

doi:10.1515/tjj.1985.2.4.273

Cited by 2 publications

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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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