Effects of Mach Number Up to 0.34 and Reynolds Number Up to 8,000,000 on the Maximum Lift Coefficient of a Wing of NACA 66-series Airfoil Sections PDF Download
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Author: G. Chester Furlong Publisher: ISBN: Category : Aerofoils Languages : en Pages : 52
Book Description
The effects of Mach numbers up to 0.34 and Reynolds number up to 8,000,000 on the maximum lift coefficient of the wing of NACA 66-weries airfoil sections are presented. The wing was tested with full-span and partial-span split flaps deflected 60 degrees and without flaps. The results indicated that the peak values of maximum lift coefficient occurred at free-stream Mach numbers of approximately 0.212 and 0.227 for the flaps-retracted configuration and 0.138 and 0.196 for the full-span flaps-deflected configuration for tunnel pressures of 33 and 14.7 pounds per square inch, respectively.
Author: G. Chester Furlong Publisher: ISBN: Category : Aerofoils Languages : en Pages : 52
Book Description
The effects of Mach numbers up to 0.34 and Reynolds number up to 8,000,000 on the maximum lift coefficient of the wing of NACA 66-weries airfoil sections are presented. The wing was tested with full-span and partial-span split flaps deflected 60 degrees and without flaps. The results indicated that the peak values of maximum lift coefficient occurred at free-stream Mach numbers of approximately 0.212 and 0.227 for the flaps-retracted configuration and 0.138 and 0.196 for the full-span flaps-deflected configuration for tunnel pressures of 33 and 14.7 pounds per square inch, respectively.
Author: G. Chester Furlong Publisher: ISBN: Category : Aerofoils Languages : en Pages : 14
Book Description
The effects of Mach number and Reynolds number on the maximum lift coefficient of a wing of NACA 230-series airfoil sections are presented. The ranges of Mach number for the wind-tunnel tests were from 0.10 to 0.35 and from 0.08 to 0.27; the corresponding Reynolds number ranges were from 1,530,000 to 4,530,000 and from 2,450,000 to 7,880,000, respectively.
Author: E. O. Pearson Publisher: ISBN: Category : Aerodynamic load Languages : en Pages : 48
Book Description
Force and pressure-distribution measurements were made on a fighter-type wing model of conventional NACA 230-series airfoil sections in the Langley 16-foot high-speed tunnel to determine the effects of compressibility on the maximum lift characteristics and the span-wise load distribution. The range of angle of attack investigated was from -10 to +24 degrees. The Mach range of from 0.20 to 0.70 at small and medium angles of attack and from 0.15 to 0.625 at very large angles of attack. Maximum lift coefficient increased up to a Mach number of 0.3, decreased rapidly to a Mach number of 0.55, and then decreased moderately. At high speeds, maximum lift coefficient was reached at from 10 to 12 degrees beyond the stalling angle. In high-speed stalls, resultant load underwent a moderate shift outward.
Author: F. E. West Publisher: ISBN: Category : Aerofoils Languages : en Pages : 56
Book Description
The effects of compressibility on the lift, pressure, pitching-moment, and load characteristics of a 12-foot tapered wing having NACA 64-210 airfoil sections and aspect ratio of 6 is presented for Mach numbers up to 0.60 and an angle-of-attack range of -4 degrees up through the stall.
Author: WIlliam R. Bates Publisher: ISBN: Category : Aerofoils Languages : en Pages : 538
Book Description
The aerodynamic characteristics of 19 isolated tail surfaces have been determined by wind-tunnel tests and tests have also been made of rectangular airfoils of various aspect ratios with and without double end plates of various shapes. Thes data from these tests have been collected and analyzed.
Author: G. Chester Furlong
Author: G. Chester Furlong
Author: G. Chester Furlong
Author: E. O. Pearson
Author: G. Chester Furlong
Author: G. Chester Furlong
Author: F. E. West
Author: 
Author: United States. National Advisory Committee for Aeronautics
Author: WIlliam R. Bates
Author: United States. National Advisory Committee for Aeronautics