Author: William MutterperlPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
The Calculation of Span LCAD Distributions of Swept-back Wings
Author: William MutterperlThe 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: 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.
A Comparison of Span Load Distribution Calculation Methods for Swept Wings
Author: Merwin E. Spragg (CAPT, USAF.)Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 132
Book Description
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.
A Comparison of Three Theoretical Methods of Calculating Span Load Distribution on Swept Wings
Author: Nicholas H. Van DornPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 77
Book Description
It was found that (1) the Weissinger method gave good accuracy and involved by far the least computing effort and (2) the Falkner method gave the best accuracy but at considerable expense in computing effort.
Some Theoretical Low-speed Span Loading Characteristics of Swept Wings in Roll and Sideslip
Author: John D. BirdPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 44
Book Description
The 7-point method of Weissinger is used to calculate the span loading in roll, lateral center of pressure, and damping in roll for wings having various aspect ratios, sweep angles, and taper ratios. The applicability of the method to the determination of certain other aerodynamic derivatives is investigated, and corrections for the first-order effects of compressibility are indicated.
Survey of Methods for Finding Span Load Distribution for Swept-back, Inelastic Wings
Author: Kra-Jean BoribhandhPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 68
Book Description
Span Load Distributions Resulting from Angle of Attack, Rolling, and Pitching for Tapered Sweptback Wings with Streamwise Tips
Author: John C. MartinPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 143
Book Description
On the basis of the linearized supersonic-flow theory the span load distributions resulting from constant angle of attack, from steady rolling, and from steady pitching were calculated for a series of thin sweptback tapered wings with streamwise tips and with supersonic leading and trailing edges. The results are valid for the Mach number range for which the Mach line from either wing tip does not intersect the remote half-wing. The results of this analysis are presented as a series of design charts. Some illustrative variations of the spanwise distributions of circulation with the various design parameters are also presented.
Span Load Distributions Resulting from Constant Angle of Attack, Steady Rolling Velocity, Steady Pitching Velocity, and Constant Vertical Acceleration for Tapered Sweptback Wings with Streamwise Tips
Author: Margery E. HannahPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 221
Book Description
On the basis of the linearized supersonic-flow theory and theoretical spanwise distributions of circulation (which are proportional to the span load distribution) resulting from constant vertical acceleration were calculated for a series of thin, sweptback, tapered wings with streamwise tips, subsonic leading edges, and supersonic trailing edges. The results of the analysis are presented as a series of design charts. Some illustrative variations of the spanwise distributions of circulation with aspect ratio, taper ratio, Mach number, leading-edge sweepback, and axis-of-pitch location are also included.