Author: H. SchlichtingPublisher:
ISBN:
Category :
Languages : en
Pages : 90
Book Description
Calculation of Lift Distribution of Swept Wings
Author: H. SchlichtingNote on the Calculation of the 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.
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.
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.
Estimation of the Damping in Roll of Wings Through the Normal Flight Range of Lift Coefficient
Author: Alex GoodmanPublisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 38
Book Description
The development of three methods for calculating the damping in roll through the normal flight range of lift coefficient for wing plan forms having various sweep angles, aspect ratios, and taper ratios is presented and comparisons between experimental and calculated results are made.
A Simplified Mathematical Model for Calculating Aerodynamic Loading and Downwash for Midwing Wing-fuselage Combinations with Wings of Arbitrary Plan Form
Author: Martin ZlotnickPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 40
Book Description
Method for Calculating Lift Distribtutions for Unswept Wings with Flaps Or Ailerons by Use of Nonlinear Section Lift Data
Author: James C. SivellsPublisher:
ISBN:
Category : Ailerons
Languages : en
Pages : 722
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.
The Spanwise Lift Distribution of Swept Wings at Subsonic Speeds
Author: Eli Herman BensteinPublisher:
ISBN:
Category : Air flow
Languages : en
Pages : 124
Book Description
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.