The Calculation Of Span Load Distributions On Swept Back Wings
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The Calculation Of Span Load Distributions On Swept Back Wings
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Author : William Mutterperl
language : en
Publisher:
Release Date : 1941
The Calculation Of Span Load Distributions On Swept Back Wings written by William Mutterperl and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1941 with Airplanes categories.
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 Calculation Of Span Lcad Distributions Of Swept Back Wings
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Author : William Mutterperl
language : en
Publisher:
Release Date : 1941
The Calculation Of Span Lcad Distributions Of Swept Back Wings written by William Mutterperl and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1941 with categories.
Theoretical Distribution Of Load Over A Swept Back Wing
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Author : Doris Cohen
language : en
Publisher:
Release Date : 1942
Theoretical Distribution Of Load Over A Swept Back Wing written by Doris Cohen and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1942 with Aerodynamic load categories.
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.
A Comparison Of Span Load Distribution Calculation Methods For Swept Wings
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Author : Merwin E. Spragg (CAPT, USAF.)
language : en
Publisher:
Release Date : 1971
A Comparison Of Span Load Distribution Calculation Methods For Swept Wings written by Merwin E. Spragg (CAPT, USAF.) and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1971 with Aerodynamic load categories.
Theoretical Span Load Distributions And Rolling Moments For Sideslipping Wings Of Arbitrary Plan Form In Incompressible Flow
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Author : M. J. Queijo
language : en
Publisher:
Release Date : 1955
Theoretical Span Load Distributions And Rolling Moments For Sideslipping Wings Of Arbitrary Plan Form In Incompressible Flow written by M. J. Queijo and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1955 with Aerodynamic load categories.
A method of computing span loads and the resulting rolling moments for sideslipping wings of arbitrary plan form in incompressible flow is derived. The method requires that the span load at zero sideslip be known for the wing under consideration. Because this information is available for a variety of wings, this requirement should not seriously restrict the application of the present method. The basic method derived herein requires a mechanical differentiation and integration to obtain the rolling moment for the general wing in sideslip. For wings having straight leading and trailing edges over each semispan, the rolling moment equation in terms of plan-form parameters and the lateral center of pressure of the lift due to angle of attack. Calculated span loads and rolling-moment parameters are compared with experimental values. The comparison indicates good agreement between calculations and available experimental data.
Span Load Distributions Resulting Fron Angle Of Attack Rolling And Pitching For Tapered Swept Back Wings With Streamwise Tips
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Author : John C. Martin
language : en
Publisher:
Release Date : 1952
Span Load Distributions Resulting Fron Angle Of Attack Rolling And Pitching For Tapered Swept Back Wings With Streamwise Tips written by John C. Martin and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1952 with Aerodynamic load categories.
On the basis of the linearized supersonic-flow theory the span load distributions resulting from constsnt angle of attack, from steady rolling and from steady pitching were calculated for a series of thin sweptback tempered 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 the analysis are presented as a series of design charts. Some illustrative variations of the spanwise distribution of circulation with the various design parameters are also presented.
A Method For Calculating The Subsonic Steady State Loading On An Airplane With A Wing Of Arbitrary Plan Form And Stiffness
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Author : W. L. Gray
language : en
Publisher:
Release Date : 1953
A Method For Calculating The Subsonic Steady State Loading On An Airplane With A Wing Of Arbitrary Plan Form And Stiffness written by W. L. Gray and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1953 with Aerodynamic load categories.
A method for computing the steady-state span load distribution on an elastic airplane wing for specified airplane weights and load factors is given. The method is based on a modification of the Weissinger L-method and applies at subcritical Mach numbers. It includes the effects of external stores and fuselage on the spanwise loading. Modifications are outlined for treating tail-boom and tailless airplane configurations and for calculating the divergence dynamic pressure of a swept wing with a large external store. A method is also outlined for reducing wind-tunnel data to obtain effective aerodynamic coefficients which are free of model flexibility effects. The effects of Mach number can readily be evaluated from the aerodynamic coefficients thus obtained.
Linearized Lifting Surface Theory For Swept Back Wings With Slender Plan Forms
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Author : Harvard Lomax
language : en
Publisher:
Release Date : 1949
Linearized Lifting Surface Theory For Swept Back Wings With Slender Plan Forms written by Harvard Lomax and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1949 with Aerodynamic load categories.
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.
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
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Author : Margery E. Hannah
language : en
Publisher:
Release Date : 1952
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 written by Margery E. Hannah and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1952 with Airplanes categories.
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.
Span Load Distributions Resulting From Angle Of Attack Rolling And Pitching For Tapered Sweptback Wings With Streamwise Tips
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Author : John C. Martin
language : en
Publisher:
Release Date : 1952
Span Load Distributions Resulting From Angle Of Attack Rolling And Pitching For Tapered Sweptback Wings With Streamwise Tips written by John C. Martin and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1952 with Airplanes categories.
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.