Add to ORKGThe lift on a bent, flat plate is calculated exactly by the use of conformal mapping. Results are presented in terms permitting direct determination of the angle of zero lift, the lift coefficient, and the lift-curve slope for any flap-chord ratio, flap-deflection angle, and angle of attack
The method of superposition of linearized conical flows has been applied to the calculation of the a...
Peer Reviewedhttp://deepblue.lib.umich.edu/bitstream/2027.42/90737/1/AIAA-2011-6527-603.pd
Tests were made on a model wing with three different sized split trailing-edged flaps, in the NACA 7...
The lift on a bent, flat plate is calculated exactly by the use of conformal mapping. Results are pr...
Previous theories and empirical formulas for the lift of flat planing surfaces are reviewed, and t...
This report presents a theoretical analysis of the lift on a trailing edge flap. An analytical expre...
This report concerns, first, the determination of the lift of a wing which is situated in a curvilin...
This report contains a new, simple method of calculating the air forces to which thin wings are subj...
.4 graphical method is deacribedjor~nding the shape (camber and twist) oj an airfoil baring an arbit...
In the subdivided wing section profile, the diagram of the current is entirely changed and the harmf...
The effect of an aileron displacement on the distribution of the lift along the span is computed for...
A method is described for using lifting-surface theory to obtain the pressure distribution on a wing...
This report gives a simple and exact method of calculating the lift distribution on thin wing sectio...
Thesis (M.S.)--Wichita State University, College of Engineering, Dept. of Aerospace Engineering.In t...
The greatest efficiency for a lifting surface at supersonic speeds, according to the theoretical con...
The method of superposition of linearized conical flows has been applied to the calculation of the a...
Peer Reviewedhttp://deepblue.lib.umich.edu/bitstream/2027.42/90737/1/AIAA-2011-6527-603.pd
Tests were made on a model wing with three different sized split trailing-edged flaps, in the NACA 7...
The lift on a bent, flat plate is calculated exactly by the use of conformal mapping. Results are pr...
Previous theories and empirical formulas for the lift of flat planing surfaces are reviewed, and t...
This report presents a theoretical analysis of the lift on a trailing edge flap. An analytical expre...
This report concerns, first, the determination of the lift of a wing which is situated in a curvilin...
This report contains a new, simple method of calculating the air forces to which thin wings are subj...
.4 graphical method is deacribedjor~nding the shape (camber and twist) oj an airfoil baring an arbit...
In the subdivided wing section profile, the diagram of the current is entirely changed and the harmf...
The effect of an aileron displacement on the distribution of the lift along the span is computed for...
A method is described for using lifting-surface theory to obtain the pressure distribution on a wing...
This report gives a simple and exact method of calculating the lift distribution on thin wing sectio...
Thesis (M.S.)--Wichita State University, College of Engineering, Dept. of Aerospace Engineering.In t...
The greatest efficiency for a lifting surface at supersonic speeds, according to the theoretical con...
The method of superposition of linearized conical flows has been applied to the calculation of the a...
Peer Reviewedhttp://deepblue.lib.umich.edu/bitstream/2027.42/90737/1/AIAA-2011-6527-603.pd
Tests were made on a model wing with three different sized split trailing-edged flaps, in the NACA 7...