A. Nastase

In this paper are presented some original spectral solutions for the three-dimensional, stationary, laminar, compressible boundary layer equations on flattened flying configurations (FC). The axial, lateral and vertical velocitys components u5, v5 and w5 in the boundary layer are here expressed in spectral forms as in (13a-c). The velocities components at the edge Ue, Ve, We of the boundary layer are obtained by using an own inviscid solver on the modified aircraft configuration after the solidification of the boundary layer. If the temperature T is eliminated from the impulse equations a quadratic algebraic system with respect to the coefficients Ui, Vi, Wi, of the spectral velocities is obtained. A semi-inverse procedure is used for the iterative solving of this system. These spectral solutions are applied for the computation of the total drag coefficient Cd(t) and the viscous design of the shape of the delta wing, via iterative optimum-optimorum theory.

9. DGLR-Fach-Symposium, Erlangen, 1994

Conference Paper

englisch

21,0 x 29,7 cm, 8 Seiten

DGLR-Bericht, 1994, 1994-04, Strömungen mit Ablösung; S.260-267; 1994; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aerodynamics, boundary layers

Bestellbar

1994