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A concept of the vortex lift of sharp-edge delta wings based on a leading-edge-suction analogy

Edward C Polhamus

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Abstract

A concept for the calculation of the vortex lift of sharp-edge delta wings is pre sented and compared with experimental data.The concept is based on an analogy between the vortex lift and the leading-edge suction associated with the potential flow about the leading edge.This concept, when combined with potential-flow theory modified to include the nonlinearities associated with the exact boundary condition and the loss of the lift component of the leading-edge suction, provides excellent prediction of the total lift for a wide range of delta wings up to angles of attack of 20° o r greater.

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A concept for the calculation of the vortex lift of sharp-edge delta wings is pre sented and compared with experimental data.The concept is based on an analogy between the vortex lift and the leading-edge suction associated with the potential flow about the leading edge.This concept, when combined with potential-flow theory modified to include the nonlinearities associated with the exact boundary condition and the loss of the lift component of the leading-edge suction, provides excellent prediction of the total lift for a wide range of delta wings up to angles of attack of 20° o r greater.

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Available abstract

A concept for the calculation of the vortex lift of sharp-edge delta wings is pre sented and compared with experimental data.The concept is based on an analogy between the vortex lift and the leading-edge suction associated with the potential flow about the leading edge.This concept, when combined with potential-flow theory modified to include the nonlinearities associated with the exact boundary condition and the loss of the lift component of the leading-edge suction, provides excellent prediction of the total lift for a wide range of delta wings up to angles of attack of 20° o r greater.

Key concepts: Lift (data mining), Vortex, Vortex lift, Delta wing, Leading edge, Suction, Mechanics, Potential flow

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