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
The chordwise distribution theory was taken over from the theory of the infinite wing. Since in this...
A graphical method is described for finding the shape (camber and twist) of an airfoil having an arb...
In calculating the self-induction of a wing surface, elliptical lift distribution is assumed, while ...
The approximation method described makes possible lift-distribution computations in a few minutes. C...
The method for determination of the spanwise lift distribution is based on the Fourier series for th...
An examination is made in this paper of a number of methods for calculating the spanwise load distri...
A method is presented which allows the use of nonlinear section lift data in the calculation of the ...
A method is presented for calculating wing characteristics by lifting-line theory using nonlinear se...
A method is presented for calculating wing characteristics by lifting-line theory using nonlinear se...
Tables are given for determining the load distribution of tapered wings with partial-span flaps plac...
A method is presented for calculating lift distributions for unswept wings with flaps or ailerons us...
As a rule, the actual lift distribution at the wing tips shows deviations from the theoretical distr...
The finite-step method was programmed for computing the span loading and stability derivatives of tr...
Spanwise lift distributions have been calculated for nineteen unswept wings with various aspect rati...
The effect of an aileron displacement on the distribution of the lift along the span is computed for...
The chordwise distribution theory was taken over from the theory of the infinite wing. Since in this...
A graphical method is described for finding the shape (camber and twist) of an airfoil having an arb...
In calculating the self-induction of a wing surface, elliptical lift distribution is assumed, while ...
The approximation method described makes possible lift-distribution computations in a few minutes. C...
The method for determination of the spanwise lift distribution is based on the Fourier series for th...
An examination is made in this paper of a number of methods for calculating the spanwise load distri...
A method is presented which allows the use of nonlinear section lift data in the calculation of the ...
A method is presented for calculating wing characteristics by lifting-line theory using nonlinear se...
A method is presented for calculating wing characteristics by lifting-line theory using nonlinear se...
Tables are given for determining the load distribution of tapered wings with partial-span flaps plac...
A method is presented for calculating lift distributions for unswept wings with flaps or ailerons us...
As a rule, the actual lift distribution at the wing tips shows deviations from the theoretical distr...
The finite-step method was programmed for computing the span loading and stability derivatives of tr...
Spanwise lift distributions have been calculated for nineteen unswept wings with various aspect rati...
The effect of an aileron displacement on the distribution of the lift along the span is computed for...
The chordwise distribution theory was taken over from the theory of the infinite wing. Since in this...
A graphical method is described for finding the shape (camber and twist) of an airfoil having an arb...
In calculating the self-induction of a wing surface, elliptical lift distribution is assumed, while ...