Author: H. SchlichtingPublisher:
ISBN:
Category :
Languages : en
Pages : 131
Book Description
Note on the Calculation of the Lift Distribution of Swept Wings
Author: H. SchlichtingCalculation of Lift Distribution of Swept Wings
Author: H. SchlichtingThe Lift Distribution of Swept-back Wings
Author: United States. Air Force. Air Matériel CommandPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 40
Book Description
Two procedures for calculating the lift distribution along the span are given, in which better account is taken of the distribution of circulation over the area than in the Prandtl lifting-line theory. The methods are also applicable to wings with sweepback. Calculated results according to two methods agree excellently. Using the second, simpler method one needs about 3 hours for the calculation of the lift distribution of a straight wing, and about eight hours for this calculation for the swept-back wing. The results are compared with those of the Multhopp method and with experimental results. Finally there is a brief not on the swept-back wing in sideslip.
The Calculation of Span Load Distributions on Swept-back Wings
Author: William MutterperlPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 28
Book Description
Span load distributions of swept-back wings have been calculated. The method used was to replace the wing with a bound vortex at the quarter-chord line and to calculate the downwash due to the system of bound and trailing vortices to conform at the three-quarter-chord line to the slope of the flat-plate wing surface. Results are given for constant-chord and 5:1 tapered plan forms, for swee-pback angles of 0, 30 and 45 degresss, and for aspect ratios of 3, 6, and 9. Some comments on the stalling of swept-back wings are included.
The Lift Distribution of Swept-back Wings
Author: J. WeissingerPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 51
Book Description
Two procedures for calculating the lift distribution along the span are given in which a better account is taken of the distribution of circulation over te area than in the Prandtl lifting-line theory. The methods are also applicable to wing sweepback. Calculated results for the two methods were in agreement.
The Spanwise Lift Distribution of Swept Wings at Subsonic Speeds
Author: Eli Herman BensteinPublisher:
ISBN:
Category : Air flow
Languages : en
Pages : 124
Book Description
Calculation of the Twist Distribution of Wings Designed for Cruise at Transonic Speeds
Author: Michael J. MannPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 36
Book Description
Method for Calculating the Rolling and Yawing Moments Due to Rolling for Unswept Wings with Or Without Flaps Or Ailerons by Use of Nonlinear Section Lift Data
Author: Albert P. MartinaPublisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 52
Book Description
The methods of NACA Reports 865 and 1090 have been applied to the calculation of the rolling- and yawing-moment coefficients due to rolling for unswept wings with or without flaps or ailerons. The methods allow the use of nonlinear section lift data together with lifting-line theory. Two calculated examples are presented in simplified computing forms in order to illustrate the procedures involved.
Method for Calculating Lift Distributions for Unswept Wings with Flaps Or Ailerons by Use of Nonlinear Section Lift Data
Author: James C. SivellsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 70
Book Description
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 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.
Linearized Lifting-surface Theory for Swept-back Wings with Slender Plan Forms
Author: Harvard LomaxPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 48
Book Description
The spanwise and chordwise distribution of loading, the lift, and the induced drag of a swept-back wing of slender plan form are developed by means of linearized lifting-surface theory. The results are applicable for all free-stream Mach numbers. The term slender implies that the ratio of the reduced span to over-all length of the wing is small.