Effects of Spanwise Thickness Variation on the Transonic Aerodynamic Characteristics of Wings Having 35 Degrees of Sweepback, Aspect Ratio 4, and Taper Ratio 0.60 PDF Download
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Author: William D. Morrison Publisher: ISBN: Category : Aerodynamics, Transonic Languages : en Pages : 21
Book Description
An investigation has been conducted in the Langley high-speed 7- by 10-foot tunnel to determine the effects of a spanwise variation in thickness ratio on the aerodynamic characteristics of a wing having a plan form identical to that of a constant-percent thickness-ratio wing previously investigated as part of an extensive transonic research program. The wing with thickness variation had 35 degrees of sweepback, aspect ratio 4, and taper ratio 0.60, with airfoil section (parallel to the free stream) tapered from an NACA 65A006 section at root chord to an NACA 65A002 section at the tip chord. The test Mach number range was from 0.60 to 1.08 at Reynolds numbers of the order 0f 650,000.
Author: William D. Morrison Publisher: ISBN: Category : Aerodynamics, Transonic Languages : en Pages : 21
Book Description
An investigation has been conducted in the Langley high-speed 7- by 10-foot tunnel to determine the effects of a spanwise variation in thickness ratio on the aerodynamic characteristics of a wing having a plan form identical to that of a constant-percent thickness-ratio wing previously investigated as part of an extensive transonic research program. The wing with thickness variation had 35 degrees of sweepback, aspect ratio 4, and taper ratio 0.60, with airfoil section (parallel to the free stream) tapered from an NACA 65A006 section at root chord to an NACA 65A002 section at the tip chord. The test Mach number range was from 0.60 to 1.08 at Reynolds numbers of the order 0f 650,000.
Author: William D. Morrison Publisher: ISBN: Category : Aerodynamics Languages : en Pages : 38
Book Description
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: Ralph P. Bielat Publisher: ISBN: Category : Aerodynamics, Transonic Languages : en Pages : 44
Book Description
Four wing-body combinations of the same plan form (47 degree sweep, 3.5 aspect ratio, and 0.2 taper ratio) were compared at transonic speeds in the Langley 8-foot high-speed tunnel. Three wings were 4, 6, and 9 percent thick; the fourth was 6 percent thick but, on the inner 0.4 span, tapered to 12-percent thickness at the roots.
Author: Albert G. Few Publisher: ISBN: Category : Airplanes Languages : en Pages : 107
Book Description
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: Edward J. Hopkins Publisher: ISBN: Category : Aerodynamic load Languages : en Pages : 40
Book Description
Lift, pitching-moment, and pressure distribution were measured on a wing which was swept -40, -30, 0, 35, and 45 degrees. The wing span was decreased to give aspect ratios 6.8, 5.3, 4.2, 3.4, and 2.8. The effects of independent variations of sweep and aspect ratio on the lift, pitching-moment, and span-load characteristics of the wings are compared with the effects estimated by use of the Weissinger method.
Author: Ralph P. Bielat Publisher: ISBN: Category : Aerodynamics, Transonic Languages : en Pages : 38
Book Description
Four wing-body combinations of the same plan form (47 degree sweep, 3.5 aspect ratio, and 0.2 taper ratio) were compared at transonic speeds in the Langley 8-foot high-speed tunnel. Three wings were 4, 6, and 9 percent thick; the fourth was 6 percent thick but, on the inner 0.4 span, tapered to 12-percent thickness at the roots.
Author: Edward C. Polhamus Publisher: ISBN: Category : Aerodynamics Languages : en Pages : 90
Book Description
A summary and analysis has been made of results obtained in a systematic research program concerned with the effects of wing sweep, aspect ratio, taper ratio, and dihedral on the rolling moment due to sideslip characteristics of wing-fuselage configurations up to Mach numbers of about 0.95. Other test results are presented to show trends of rolling moment due to sideslip with Mach number for a few wings in the transonic and supersonic speed range.
Author: William D. Morrison Publisher: ISBN: Category : Aerodynamics, Transonic Languages : en Pages : 22
Book Description
An investigation has been conducted in the Langley High-Speed 7- by 10-foot tunnel to determine the transonic aerodynamic characteristics of a wing having a spanwise variation in thickness ratio. The wing investigated had 45 degrees of sweepback, aspect ratio 8, taper ratio of 0.45, and airfoil sections tapered from an NACA 63A010 section at the root chord to an NACA 63A006 section at the tip chord. The test Mach number range was from 0.60 to 1.05 at Reynolds numbers of the order of 500,000.
Author: William D. Morrison
Author: William D. Morrison
Author: William D. Morrison
Author: Ralph P. Bielat
Author: Albert G. Few
Author: Edward J. Hopkins
Author: Joseph W. Cleary
Author: Ralph P. Bielat
Author: Edward C. Polhamus
Author: William D. Morrison
Author: