Effects Of Three Spanwise Twist Variations On The Longitudinal Aerodynamic Characteristics Of A Thin 45 Deg Sweptback Highly Tapered Wing At Transonic Speeds PDF Download
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Author | : |
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Total Pages | : 44 |
Release | : 1959 |
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Download Effects of Three Spanwise Twist Variations on the Longitudinal Aerodynamic Characteristics of a Thin 45 Deg Sweptback Highly Tapered Wing at Transonic Speeds Book in PDF, ePub and Kindle
Author | : John P. Mugler |
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Total Pages | : 50 |
Release | : 1959 |
Genre | : Airplanes |
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Download Effects of Three Spanwise Twist Variations on the Longitudinal Aerodynamic Characteristics of a Thin 45° Sweptback Highly Tapered Wing at Transonic Speeds Book in PDF, ePub and Kindle
Author | : John P. Jr Mugler |
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Total Pages | : 40 |
Release | : 1959 |
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Download Effects of Three Spanway Twist Variations of the Longitudinal Aerodynamic Characteristics of a Thin 45 Sweptback Highly Tapered Wing at Transonic Speeds Book in PDF, ePub and Kindle
Author | : William D. Morrison |
Publisher | : |
Total Pages | : 38 |
Release | : 1951 |
Genre | : Aerodynamics |
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Download Effects of Spanwise Thickness Variation on the Aerodynamic Characteristics of 35 Degree and 45 Degree Sweptback Wings of Aspect Ratio 6 Book in PDF, ePub and Kindle
An aerodynamic investigation has been conducted in the Langley high-speed 7- by 10-foot tunnel to determine the effects of taper-in-thickness on the aerodynamics characteristics of wings having 35 and 45 degrees of sweep-back, aspect ratio 6, and taper ratio 0.60. The wings were tapered from NACA 65A009 airfoil sections at the root chord to NACA 65A003 airfoil sections at the tip chord. The test Mach number range was from 0.60 to 1.14 at a Reynolds number of the order of 500,000.
Author | : George L. Pratt |
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Total Pages | : 110 |
Release | : 1952 |
Genre | : Airplanes |
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Download Effects of Twist and Camber on the Low-speed Longitudinal Stability Characteristics of a 45© Swept-back Wing of Aspect Ratio 8 at Reynolds Numbers from 1.5 X 106 to 4.8 X 10 as Determined by Pressure Distributions, Force Tests, and Calculations Book in PDF, ePub and Kindle
Author | : Albert G. Few |
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Total Pages | : 107 |
Release | : 1954 |
Genre | : Airplanes |
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Download Effects of Sweep and Thickness on the Static Longitudinal Aerodynamic Characteristics of a Series of Thin, Low-aspect-ratio, Highly Tapered Wings at Transonic Speeds Book in PDF, ePub and Kindle
The effects on drag and lift-drag ratio of a variation in sweep angle from -14.03 degrees to 45 degrees with respect to the quarter-chord line for wings of 3-percent-chord thickness was found to be small in comparison to the effects of a variation in thickness from 2 percent chord to 4.5 percent chord for wings with 14.03 degree sweepback.
Author | : Lynn W. Hunton |
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Total Pages | : 36 |
Release | : 1950 |
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Download Effects of Twist and Camber on the Low-speed Characteristics of a Large-scale 45 Degree Swept-back Wing Book in PDF, ePub and Kindle
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Total Pages | : 0 |
Release | : 1952 |
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Download Effect of Linear Spanwise Variations of Twist and Circular-Arc Camber on Low-Speed Static Stability, Rolling, and Yawing Characteristics of a 45 Degrees Sweptback Wing of Aspect Ratio 4 and Taper Ration 0.6 Book in PDF, ePub and Kindle
An investigation at low scale has been made in the Langley stab unity tunnel in order to determine the effect of linear spanwise variations of twist and circular-arc camber on the low-speed aerodynamic characteristics and static-stability and rotary-stability (rolling and yawing) derivatives of a wing of aspect ratio 4, taper ratio 0.6, and with 45 deg sweepback of the quarter-chord line. Results of the investigation indicate that twist or camber produced only small changes in the maximum lift coefficient. A combination of camber and twist was more effective than twist alone in providing an increase in the maximum lift-to-drag ratio in the moderate lift-coefficient range for the wings investigated. The variation of static longitudinal stability through the lift-coefficient range was less for the twisted wing than for the twisted and cambered or plane wing. A combination of twist and camber generally extended the initial linear range of several of the static- and rotary-stability derivatives to a higher lift coefficient and, although these effects were small, higher Reynolds numbers may result in larger effects.
Author | : Frederick C. Grant |
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Total Pages | : 18 |
Release | : 1957 |
Genre | : Aerodynamic load |
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Download Span Loadings Due to Wing Twist at Transonic and Supersonic Speeds Book in PDF, ePub and Kindle
Two similar tapered sweptback plan forms with the same two spanwise variations of twist have been tested in the Mach number range from 0.8 to 2.0. The test results showed, in general, rather good agreement with theoretical predictions of the incremental span loadings due to twist for zero angle of attack. The measured incremental span loadings due to twist generally diminished with increasing angle of attack through the Mach number range. At a Mach number of 0.9, the incremental loadings progressively vanished from the tip inboard with increasing angle of attack. For the highest angles of attack (about 20 degrees) at Mach number 0.9, there was no difference in the span loadings of the flat and twisted wings. At a higher supersonic speeds, a similar vanishing at the tips of the incremental loading due to twist was starting at the highest angles of attack (near 20 degrees).
Author | : Emma Jean Landrum |
Publisher | : |
Total Pages | : 52 |
Release | : 1961 |
Genre | : Aerodynamic load |
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Download Effects at Mach Numbers of 1.61 and 2.01 of Camber and Twist on the Aerodynamic Characteristics of Three Swept Wings Having the Same Planform Book in PDF, ePub and Kindle