Open Access
A computer program for calculating aerodynamic characteristics of low aspect-ratio wings with partial leading-edge separation
S. C. Mehrotra,C. E. Lan +1 more
Reads0
Chats0
TLDR
In this article, the necessary information for using a computer program to predict distributed and total aerodynamic characteristics for low aspect ratio wings with partial leading-edge separation is presented, where the flow is assumed to be steady and inviscid.Abstract:
The necessary information for using a computer program to predict distributed and total aerodynamic characteristics for low aspect ratio wings with partial leading-edge separation is presented. The flow is assumed to be steady and inviscid. The wing boundary condition is formulated by the Quasi-Vortex-Lattice method. The leading edge separated vortices are represented by discrete free vortex elements which are aligned with the local velocity vector at midpoints to satisfy the force free condition. The wake behind the trailing edge is also force free. The flow tangency boundary condition is satisfied on the wing, including the leading and trailing edges. The program is restricted to delta wings with zero thickness and no camber. It is written in FORTRAN language and runs on CDC 6600 computer.read more
Citations
More filters
Theoretical study of aerodynamic characteristics of wings having vortex flow
TL;DR: In this paper, the aerodynamic characteristics of slender wings having separation induced vortex flows are investigated by employing three different computer codes: free vortex sheet, quasi vortex lattice, and suction analogy methods.
References
More filters
Subsonic aerodynamic characteristics of interacting lifting surfaces with separated flow around sharp edges predicted by a vortex-lattice method
J. E. Lamar,B. B. Gloss +1 more
TL;DR: In this paper, the authors applied the vortex-lattice method to computing side-edge suction force for isolated or interacting planforms, and found that the results obtained for a number of different isolated planforms produced acceptable agreement with results obtained from a method employing continuous induced-velocity distributions.
Related Papers (5)
A theoretical investigation of the aerodynamics of low-aspect-ratio wings with partial leading-edge separation
S. C. Mehrotra,C. E. Lan +1 more
Development of a Viscous Vortex/Wing Interaction Program for Thick Wings with Rounded Leading Edge.
Charles J Dixon,S Sampath +1 more