Add to ORKGA new method has been developed by which the mean camber surface can be determined for trimmed noncoplanar planforms with minimum vortex drag under subsonic conditions. The method uses a vortex lattice and overcomes previous difficulties with chord loading specification; it uses a Trefftz plane analysis to determine the optimum span loading for minimum drag, then solves for the mean camber surface of the wing which will provide the required loading. Pitching-moment or root-bending-moment constraints can be employed as well at the design lift coefficient. Sensitivity studies of vortex-lattice arrangement have been made with this method and are presented. Comparisons with other theories show generally good agreement. The versatility of the me...
One of the problems connected with the sweptback wing is the difficulty of controlling the location ...
A survey was made of research on the alleviation of the trailing vortex hazard by altering span load...
A method for computing the lifting pressure distribution on a wing with partial span, swept control ...
A new subsonic method has been developed by which the mean camber surface can be determined for trim...
A survey of research on drag-due-to-lift minimization at supersonic speeds, including a study of the...
A numerical method, based on linearized theory, for designing minimum-drag supersonic wing camber su...
The aerodynamic design of a wind-tunnel model of a wing representative of that of a subsonic jet tra...
A simple unified numerical method applicable to non-planar subsonic aircraft has been developed for ...
A subsonic, linearized aerodynamic theory, wing design program for one or two planforms was develope...
The objective of this paper is to describe theoretical procedures which can be utilized by the gener...
Numerical solution for minimum induced drag, and associated loading, of nonplanar wing
During early phases of wing design, analytic and low-fidelity methods are often used to identify pro...
The tapered wing shape increases the lift in the middle of the wing and thus reduces the bending mom...
The problem of the minimum induced drag of wings having a given lift and a given span is extended to...
This paper presents a new non-linear formulation of the classical Vortex Lattice Method (VLM) approa...
One of the problems connected with the sweptback wing is the difficulty of controlling the location ...
A survey was made of research on the alleviation of the trailing vortex hazard by altering span load...
A method for computing the lifting pressure distribution on a wing with partial span, swept control ...
A new subsonic method has been developed by which the mean camber surface can be determined for trim...
A survey of research on drag-due-to-lift minimization at supersonic speeds, including a study of the...
A numerical method, based on linearized theory, for designing minimum-drag supersonic wing camber su...
The aerodynamic design of a wind-tunnel model of a wing representative of that of a subsonic jet tra...
A simple unified numerical method applicable to non-planar subsonic aircraft has been developed for ...
A subsonic, linearized aerodynamic theory, wing design program for one or two planforms was develope...
The objective of this paper is to describe theoretical procedures which can be utilized by the gener...
Numerical solution for minimum induced drag, and associated loading, of nonplanar wing
During early phases of wing design, analytic and low-fidelity methods are often used to identify pro...
The tapered wing shape increases the lift in the middle of the wing and thus reduces the bending mom...
The problem of the minimum induced drag of wings having a given lift and a given span is extended to...
This paper presents a new non-linear formulation of the classical Vortex Lattice Method (VLM) approa...
One of the problems connected with the sweptback wing is the difficulty of controlling the location ...
A survey was made of research on the alleviation of the trailing vortex hazard by altering span load...
A method for computing the lifting pressure distribution on a wing with partial span, swept control ...