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2011•Engineering and Technology JournalOpen access

Aerodynamic Parameters Analysis of Transonic Flow Past Unswept and Swept Wings

Raad Shehab Ahmed

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Abstract

The transonic flow past unswept and swept wings has been studied. For thispurpose the transonic potential flow equation is solved for inviscid compressible flow.The shock waves are replaced by discontinuities across which the entropy isconserved. The velocity field and pressure coefficients are estimated as function offree stream Mach number. The results show the effect of free stream Mach number onshock waves location and the velocity field around the wing section. The Eulersolution and potential flow solutions are identical at subsonic flow; however, atsupersonic flow the potential theory can no longer predict the flow field correctly. Theresults show the important effect of sweep angle on the value of the critical Machnumber for wings. By using Visual foil plus the pressure distribution and liftcoefficient and Mach contours for flow Past a NACA 0012 airfoil can be predicted.

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The transonic flow past unswept and swept wings has been studied. For thispurpose the transonic potential flow equation is solved for inviscid compressible flow.The shock waves are replaced by discontinuities across which the entropy isconserved. The velocity field and pressure coefficients are estimated as function offree stream Mach number. The results show the effect of free stream Mach number onshock waves location and the velocity field around the wing section. The Eulersolution and potential flow solutions are identical at subsonic flow; however, atsupersonic flow the potential theory can no longer predict the flow field correctly. Theresults show the important effect of sweep angle on the value of the critical Machnumber for wings. By using Visual foil plus the pressure distribution and liftcoefficient and Mach contours for flow Past a NACA 0012 airfoil can be predicted.

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Available abstract

The transonic flow past unswept and swept wings has been studied. For thispurpose the transonic potential flow equation is solved for inviscid compressible flow.The shock waves are replaced by discontinuities across which the entropy isconserved. The velocity field and pressure coefficients are estimated as function offree stream Mach number. The results show the effect of free stream Mach number onshock waves location and the velocity field around the wing section. The Eulersolution and potential flow solutions are identical at subsonic flow; however, atsupersonic flow the potential theory can no longer predict the flow field correctly. Theresults show the important effect of sweep angle on the value of the critical Machnumber for wings. By using Visual foil plus the pressure distribution and liftcoefficient and Mach contours for flow Past a NACA 0012 airfoil can be predicted.

Key concepts: Transonic, Aerodynamics, Geology, Flow (mathematics), Aerospace engineering, Structural engineering, Mechanics, Physics

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