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• W1497488004 abstract "Introduction V ARIOUS conceptual designs for a commercial supersonic transport have been developed in recent years. Most of these configurations have been designed using linearized and modified linearized potential theory methodologies to define the vehicle shape and the aerodynamic characteristics. Other methods based on Whitham's modified linear theory^ have been used in the design and analysis of low-boom configurations. The combination of these methods has proven to be useful in the preliminary design stage of low-boom, high-speed civil transport configurations. In estimating the overall aerodynamic characteristics of a configuration with nacelles, the interference effects must be evaluated. The lift induced by nacelles on the wing lower surface adds to the equivalent body area distributions composed of volume and lift contributions. The equivalent body area rule defines Whitham's F-function, which in turn renders the far-field overpressure signatures of a supersonic aircraft. The computational technique described in Ref. 4 provides estimations of the loads imposed on a wing surface by nacelles mounted nearby. This numerical method, however, is impaired by its inability to account for certain nonlinear effects inherent in complicated flows. The qualitative analyses of wind-tunnel data for various aircraft models with nacelles have suggested that the interference pressures, calculated using the computer program of Ref. 4, might be underestimated in the extreme near field. Therefore, more accurate estimates of the extreme near-field conditions are required to improve the design of low-boom supersonic transport configurations. The purpose of the present study is to perform NavierStokes calculations in order to provide pressure distributions and force data on a flat plate with a nacelle in close proximity. The pressure distributions obtained using Navier-Stokes equations are then compared with the pressure distributions obtained using the linear theory of Ref. 4. Incorporating the nacelle-induced lift on the wing into the design process of a low-boom transport configuration will be included in a followup study. The Navier-Stokes equations are solved by an implicit, approximately factored, finite volume, upwind algorithm. ) Baysal et al. have used this algorithm to compute a supersonic flow past an ogive-nose-cylinder at zero-deg angle of attack near a flat plate on a composite mesh of over-" @default.
• W1497488004 created "2016-06-24" @default.
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• W1497488004 date "1995-09-01" @default.
• W1497488004 modified "2023-09-25" @default.
• W1497488004 title "Viscous flow past a nacelle in proximity to a flat plate" @default.
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• W1497488004 doi "https://doi.org/10.2514/3.46847" @default.
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