Add to ORKGA method is presented for calculating lift distributions for unswept wings with flaps or ailerons using nonlinear section lift data. This method is based upon lifting-line theory and is an extension to the method described by NACA Report 865. Simplified computing forms containing detailed examples are given for both symmetrical and asymmetrical lift distributions. A few comparisons of experimental and calculated characteristics are also presented.NACA TN No. 2283."January 1951."Includes bibliographical references.A method is presented for calculating lift distributions for unswept wings with flaps or ailerons using nonlinear section lift data. This method is based upon lifting-line theory and is an extension to the method described by NACA ...
Charts and approximate formulas are presented for the estimation of static aeroelastic effects on th...
The manner in which the effects of thickness on the lift distribution are calculated in NACA Report ...
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 ...
A method is presented which allows the use of nonlinear section lift data in the calculation of the ...
The methods of NACA Reports 865 and 1090 have been applied to the calculation of the rolling- and ya...
As a rule, the actual lift distribution at the wing tips shows deviations from the theoretical distr...
The methods of NACA Reports 865 and 1090 have been applied to the calculation of the rolling- and ya...
Calculation results for 11 different finite span wings are presented. Calculations were made by a co...
A method is presented for estimating the lift due to flap deflection at low angles of attack in inco...
In this article history and development of calculation methods of wing characteristics are presented...
A method is presented for calculating wing characteristics by lifting-line theory using nonlinear se...
A method is described for using lifting-surface theory to obtain the pressure distribution on a wing...
Further use of the method gives downwash in the pi vertical center of the wake of the wing.A procedu...
The spanwise and chordwise distribution of loading, the lift, and the induced drag of a swept-back w...
Charts and approximate formulas are presented for the estimation of static aeroelastic effects on th...
The manner in which the effects of thickness on the lift distribution are calculated in NACA Report ...
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 ...
A method is presented which allows the use of nonlinear section lift data in the calculation of the ...
The methods of NACA Reports 865 and 1090 have been applied to the calculation of the rolling- and ya...
As a rule, the actual lift distribution at the wing tips shows deviations from the theoretical distr...
The methods of NACA Reports 865 and 1090 have been applied to the calculation of the rolling- and ya...
Calculation results for 11 different finite span wings are presented. Calculations were made by a co...
A method is presented for estimating the lift due to flap deflection at low angles of attack in inco...
In this article history and development of calculation methods of wing characteristics are presented...
A method is presented for calculating wing characteristics by lifting-line theory using nonlinear se...
A method is described for using lifting-surface theory to obtain the pressure distribution on a wing...
Further use of the method gives downwash in the pi vertical center of the wake of the wing.A procedu...
The spanwise and chordwise distribution of loading, the lift, and the induced drag of a swept-back w...
Charts and approximate formulas are presented for the estimation of static aeroelastic effects on th...
The manner in which the effects of thickness on the lift distribution are calculated in NACA Report ...
The approximation method described makes possible lift-distribution computations in a few minutes. C...