Summary
The paper presents two design methodologies for supersonic wing sections with hybrid laminar flow control, one for the inner wing and one for the outer wing. For the inner wing with subsonic leading edge an inviscid method with a conical flow approximation is used to determine the pressure distribution for the boundary layer computation. The Tollmien-Schlichting and crossflow instabilities are computed with a database method. Suction distributions are optimized in order to reduce friction drag at minimum suction flow rate. For the outer wing the approach is based on coupled Euler/boundary layer flow simulation and linear stability analysis for transition prediction. The investigations show that combinations of simple pressure distribution shapes can be used to optimize airfoils for maximum extent of laminar flow and hence minimum friction drag.
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© 2001 Springer-Verlag Berlin Heidelberg
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Traoré, A., Lemée, P. (2001). Laminar Design for Supersonic Civil Transport. In: Thiede, P. (eds) Aerodynamic Drag Reduction Technologies. Notes on Numerical Fluid Mechanics (NNFM), vol 76. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-45359-8_16
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DOI: https://doi.org/10.1007/978-3-540-45359-8_16
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-642-07541-4
Online ISBN: 978-3-540-45359-8
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