Add to ORKGA method introduced by Munk is extended to prove that the light-curve slope of thin wings in either subsonic flow or supersonic flow is the same when the direction of flight of the wing is reversed. It is also shown that the wing reversal does not change the thickness drag, damping-in-roll parameter or the damping-in-pitch parameter
Low-aspect-ratio wings having pointed plan forms are treated on the assumption that the flow potenti...
A theory is developed for the airfoil of finite span at supersonic speed analogous to the Prandtl ai...
The report presents a new treatment, due essentially to von Karman, of the problem of the thin airfo...
The present paper makes use of and extends a paper by Munk in which simple dynamic concepts are used...
A method introduced by Munk is extended to prove that the light-curve slope of thin wings in either ...
The well-known methods of thin-airfoil theory have been extended to oblique or sweptback airfoils of...
A previous report gave calculations for the pressure distribution over thin oblique airfoils at supe...
On the basis of linearized supersonic-flow theory, generalized equations were derived and calculatio...
The investivation is made for thin flate-plate wings for steady vertical and longitudinal motions, s...
Design curves are presented which permit rapid estimation of the lift-curve slope and damping-in-rol...
Indicial aerodynamic influence coefficients were evaluated from potential theory for a thin, flexibl...
The shock expansion method of the NACA TN No. 1143 was used to determine the principal aerodynamic c...
The point-source-distribution method of calculating the aerodynamic coefficients of thin wings at su...
The stability derivatives valid for a limited range of supersonic speeds are presented for a series ...
The well-known methods of thin-airfoil theory have been extended to oblique or sweptback airfoils of...
Low-aspect-ratio wings having pointed plan forms are treated on the assumption that the flow potenti...
A theory is developed for the airfoil of finite span at supersonic speed analogous to the Prandtl ai...
The report presents a new treatment, due essentially to von Karman, of the problem of the thin airfo...
The present paper makes use of and extends a paper by Munk in which simple dynamic concepts are used...
A method introduced by Munk is extended to prove that the light-curve slope of thin wings in either ...
The well-known methods of thin-airfoil theory have been extended to oblique or sweptback airfoils of...
A previous report gave calculations for the pressure distribution over thin oblique airfoils at supe...
On the basis of linearized supersonic-flow theory, generalized equations were derived and calculatio...
The investivation is made for thin flate-plate wings for steady vertical and longitudinal motions, s...
Design curves are presented which permit rapid estimation of the lift-curve slope and damping-in-rol...
Indicial aerodynamic influence coefficients were evaluated from potential theory for a thin, flexibl...
The shock expansion method of the NACA TN No. 1143 was used to determine the principal aerodynamic c...
The point-source-distribution method of calculating the aerodynamic coefficients of thin wings at su...
The stability derivatives valid for a limited range of supersonic speeds are presented for a series ...
The well-known methods of thin-airfoil theory have been extended to oblique or sweptback airfoils of...
Low-aspect-ratio wings having pointed plan forms are treated on the assumption that the flow potenti...
A theory is developed for the airfoil of finite span at supersonic speed analogous to the Prandtl ai...
The report presents a new treatment, due essentially to von Karman, of the problem of the thin airfo...