Add to ORKGCharts and approximate formulas are presented for the estimation of static aeroelastic effects on the spanwise lift distribution, rolling-moment coefficient, and rate of roll due to aileron deflections on swept and unswept wings at subsonic and supersonic speeds. Some design considerations brought out by the results of this paper are discussed.NACA TN No. 2747."July 1952."Includes bibliographical references.Charts and approximate formulas are presented for the estimation of static aeroelastic effects on the spanwise lift distribution, rolling-moment coefficient, and rate of roll due to aileron deflections on swept and unswept wings at subsonic and supersonic speeds. Some design considerations brought out by the results of this paper are dis...
The development of three methods for calculating the damping in roll through the normal flight range...
The methods of NACA Reports 865 and 1090 have been applied to the calculation of the rolling- and ya...
Further use of the method gives downwash in the pi vertical center of the wake of the wing.A procedu...
Charts and approximate formulas are presented for the estimation of static aeroelastic effects on th...
Charts and approximate formulas are presented for the estimation of aeroelastic effects on the spanw...
A method of modifying existing correction factors of lifting-surface theory to account approximately...
A method of modifying existing correction factors of lifting-surface theory to account approximately...
A series of untapered, unswept, complete wings of apsect ratios 1.13, 2.13, 4.13, and 6.13 was inves...
A simplified lifting-surface theory that includes effects of compressibility and spanwise variation ...
Design curves are presented which permit rapid estimation of the lift-curve slope and damping-in-rol...
Lift, pitching-moment, and pressure distribution were measured on a wing which was swept -40, -30, 0...
A method similar to that of NACA rep. 1000 is presented for calculating the effectiveness and the re...
Results and discussion are presented of a low-speed lateral-control investigation of three untapered...
A method is presented for determining the rolling and yawing moments of swept-back wings in steady s...
A method is presented for calculating the steady-state rolling effectiveness of ~lexible sweptback w...
The development of three methods for calculating the damping in roll through the normal flight range...
The methods of NACA Reports 865 and 1090 have been applied to the calculation of the rolling- and ya...
Further use of the method gives downwash in the pi vertical center of the wake of the wing.A procedu...
Charts and approximate formulas are presented for the estimation of static aeroelastic effects on th...
Charts and approximate formulas are presented for the estimation of aeroelastic effects on the spanw...
A method of modifying existing correction factors of lifting-surface theory to account approximately...
A method of modifying existing correction factors of lifting-surface theory to account approximately...
A series of untapered, unswept, complete wings of apsect ratios 1.13, 2.13, 4.13, and 6.13 was inves...
A simplified lifting-surface theory that includes effects of compressibility and spanwise variation ...
Design curves are presented which permit rapid estimation of the lift-curve slope and damping-in-rol...
Lift, pitching-moment, and pressure distribution were measured on a wing which was swept -40, -30, 0...
A method similar to that of NACA rep. 1000 is presented for calculating the effectiveness and the re...
Results and discussion are presented of a low-speed lateral-control investigation of three untapered...
A method is presented for determining the rolling and yawing moments of swept-back wings in steady s...
A method is presented for calculating the steady-state rolling effectiveness of ~lexible sweptback w...
The development of three methods for calculating the damping in roll through the normal flight range...
The methods of NACA Reports 865 and 1090 have been applied to the calculation of the rolling- and ya...
Further use of the method gives downwash in the pi vertical center of the wake of the wing.A procedu...