Author: A. van HeemertPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Theory of the Calculation of Load-distribution for Yawed and Swept Wings in Incompressible Flow
Author: A. van HeemertThe 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.
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
Applied Mechanics Reviews
Author: Theoretical Distribution of Load Over a Swept-back Wing
Author: Doris CohenPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 14
Book Description
The load over an elliptical wing with 30 degrees sweepback has been calculated by a method, based on vortex theory, which takes account of the chordwise distribution of lifting area. The theory indicates a 14-percent loss in total lift due to the introduction of sweepback, with the greatest loss taking place at the center of the span. An increase in concentration of load at the tips is also indicated. The results are compared with the results previously obtained by somewhat simpler calculations based on the assumption of a single lifting vortex.
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.
Scientific and Technical Aerospace Reports
Author: WADC Technical Note
Author: United States. Wright Air Development DivisionPublisher:
ISBN:
Category :
Languages : en
Pages : 1576
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.
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