AERODYNAMIC COEFFICIENTS OF A CIRCULAR WING IN STEADY SUBSONIC FLOW.

A. Hauptman*, T. Miloh

*Corresponding author for this work

Research output: Contribution to journalConference articlepeer-review

Abstract

An analytic solution is presented for the linearized lifting surface problem of a thin circular wing with arbitrary twist and camber in steady incompressible flow. The analysis is based on expansion of the acceleration potential in infinite series of spheroidal harmonics. Unlike previous analyses, which involve inversion of infinite sets of linear equations of solving numerically integral equations, the present method leads to rather simple explicit expressions for the lift and moment coefficients, as well as for the spanwise lift distribution and the induced drag.

Original languageEnglish
Pages (from-to)17-24
Number of pages8
JournalIsr J Technol
Volume23
Issue number1-2
StatePublished - 1985
EventProc of the Twenty-Seventh Isr Annu Conf on Aviat and Astronaut (Sel Pap) - Tel Aviv, Isr
Duration: 27 Feb 198528 Feb 1985

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