The method for determination of the spanwise lift distribution is based on the Fourier series for the representation of the lift distribution. The lift distribution, as well as the angle of attack, is split up in four elementary distributions. The insertion of the angle-of-attack distribution in the Fourier series for the lift distribution gives a compound third series which is of particular advantage for the determination of the lift distribution. The method is illustrated in an example and supplemented by a graphical method. Lastly, the results of several comparative calculations with other methods are reported
A method is presented for estimating the lift due to flap deflection at low angles of attack in inco...
Wing pressure distribution diagrams for several angles of attack and flap deflections of 0 degrees, ...
The methods of NACA Reports 865 and 1090 have been applied to the calculation of the rolling- and ya...
The method for determination of the spanwise lift distribution is based on the Fourier series for th...
A method is presented which allows the use of nonlinear section lift data in the calculation of the ...
As a rule, the actual lift distribution at the wing tips shows deviations from the theoretical distr...
A method is presented for calculating lift distributions for unswept wings with flaps or ailerons us...
The approximation method described makes possible lift-distribution computations in a few minutes. C...
A method is presented which allows the use of nonlinear section lift data in the calculation of the ...
Three methods for calculating span load distribution, those developed by V.M Falkner, Wm. Mutterperl...
The manner in which the effects of thickness on the lift distribution are calculated in NACA Report ...
Two procedures for calculating the lift distribution along the span are given in which a better acc...
A method is presented for estimating the lift due to flap deflection at low angles of attack in inco...
Wing pressure distribution diagrams for several angles of attack and flap deflections of 0 degrees, ...
The methods of NACA Reports 865 and 1090 have been applied to the calculation of the rolling- and ya...
The method for determination of the spanwise lift distribution is based on the Fourier series for th...
A method is presented which allows the use of nonlinear section lift data in the calculation of the ...
As a rule, the actual lift distribution at the wing tips shows deviations from the theoretical distr...
A method is presented for calculating lift distributions for unswept wings with flaps or ailerons us...
The approximation method described makes possible lift-distribution computations in a few minutes. C...
A method is presented which allows the use of nonlinear section lift data in the calculation of the ...
Three methods for calculating span load distribution, those developed by V.M Falkner, Wm. Mutterperl...
The manner in which the effects of thickness on the lift distribution are calculated in NACA Report ...
Two procedures for calculating the lift distribution along the span are given in which a better acc...
A method is presented for estimating the lift due to flap deflection at low angles of attack in inco...
Wing pressure distribution diagrams for several angles of attack and flap deflections of 0 degrees, ...
The methods of NACA Reports 865 and 1090 have been applied to the calculation of the rolling- and ya...