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: John R. Spreiter Publisher: ISBN: Category : Lift (Aerodynamics) Languages : en Pages : 20
Book Description
A compilation has been made of maximum-lift-coefficient data obtained in flight with six pursuit-type airplanes embodying typical conventional and low-drag airfoils. These flight data, which cover a range of Mach numbers from 0.15 to 0.72 and of Reynolds numbers from 4,400,000 to 19,500,000, have ben analyzed together with pertinent model and airfoil data obtained in several wind tunnels.
Author: John R. Spreiter Publisher: ISBN: Category : Lift (Aerodynamics) Languages : en Pages : 20
Book Description
A compilation has been made of maximum-lift-coefficient data obtained in flight with six pursuit-type airplanes embodying typical conventional and low-drag airfoils. These flight data, which cover a range of Mach numbers from 0.15 to 0.72 and of Reynolds numbers from 4,400,000 to 19,500,000, have ben analyzed together with pertinent model and airfoil data obtained in several wind tunnels.
Author: John R. Spreiter Publisher: ISBN: Category : Airplanes Languages : en Pages : 12
Book Description
Flight tests were conducted on a pursuit airplane, which has a NACA low-drag wing, to determine the effects of Mach and Reynolds numbers on the maximum lift coefficent obtainable in gradual and abrupt stalls. Gradual stalls were made at Mach numbers from 0.145 to 0.67 and Reynolds numbers from 5,200,000 to 19,300,000. Stalls of varying degreses of abruptness were made at selected Mach numbers from 0.195 to 0.44 and Reynolds numbers from 6,370,000 to 11,300,000.
Author: Publisher: ISBN: Category : Languages : en Pages : 0
Book Description
The effects of Mach number and Reynolds number on the maximum lift coefficient of a wing of NACA 64-210 airfoil sections are presented. The wing was tested through the speed range of the Langley 19-foot pressure tunnel at two values of air pressure. The ranges of Mach number obtained were from 0.07 to 0.34 at atmospheric pressure and from 0.08 to 0.26 at a pressure of 33 pounds per square inch absolute. The corresponding Reynolds number ranges were from 0.97 x 10(exp 6) to 4.44 x 10(exp 6) and from 2.20 x 10(exp 6) to 8.10 x 10(exp 6), respectively. The tests were made with and without partial-span and full-span split flaps deflected 60 deg. Pressure-distribution measurements were obtained for all configurations. The maximum lift coefficient was a function of the two independent variables, Mach number and Reynolds number, and both parameters had an important effect on the maximum lift coefficient in the ranges investigated. The stall-progression and, consequently, the shape of the lift-curve at the stall were influenced by variations in both Mach number and Reynolds number. Peak maximum lift coefficients were measured at Mach numbers between 0.12 and 0.20, depending on the Reynolds number range and flap configuration. There was very little influence of either Mach number or Reynolds number on the maximum lift of the wing with leading-edge roughness.
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: John H. Quinn Publisher: ISBN: Category : Aerodynamics Languages : en Pages : 40
Book Description
Summary: An investigation in two NACA wind tunnels has determined the effect of Reynolds number and stream turbulence on the lift and drag characteristics of a low-drag airfoil, the NACA 653-418, a=1.0 section, particularly at low Reynolds numbers, to give an indication of the performance of low-drag wings in low-scale tests. The results are correlated with similar data for the same airfoil section in the NACA two-dimensional low-turbulence pressure tunnel to provide data over a range of Reynolds number from 0.19 to 9.0 x 106. Large increases in minimum drag coefficient were found as the Reynolds number decreased. This effect was particularly marked at Reynolds numbers below 1.5 x 106. At Reynolds numbers below 1.5 x 106, stream turbulence had little effect on the drag characteristics of the NACA 653-418 airfoil section when compared on the basis of test Reynolds number but, at higher Reynolds numbers, stream turbulence had a detrimental effect on drag. Large decreases in maximum lift coefficient were found with decreasing Reynolds number; most of this decrease was encountered at Reynolds numbers above 2.0 x 106. Marked differences in maximum lift were apparent between the results obtained at high and low turbulence. When compared on the basis of effective Reynolds number, however, fair agreement was reached between the data obtained under both turbulence conditions.
Author: O. E. Sipe (Jr.) Publisher: ISBN: Category : Aerodynamics Languages : en Pages : 476
Book Description
Force and moment data are presented from wind tunnel tests of two-dimensional symmetrical NACA 63A-Series airfoils of thickness ratios from 9 to 18 percent. The tests were conducted at Mach numbers ranging from M = .30 to M = .94 with Reynolds numbers varying from R = 2.0 X 1,000,000 to R = 9.5 X 1,000,000 and at angles of attack as high as 29 degrees. Comparisons are made, wherever possible, with NACA tests of the same or similar airfoils. The transonic similarity rule is used to evaluate the consistency of the data. (Author).
Author: James E. Fitzpatrick Publisher: ISBN: Category : Airplanes Languages : en Pages : 34
Book Description
The effects of Mach number and Reynolds number on the maximum lift coefficient of a wing of NACA 64-210 airfoil sections are presented. The wing was tested with and without partial-span and full-span slip flaps deflected 60 degrees. Peak maximum lift coefficients were measured at Mach numbers between 0.12 and 0.20, depending on the Reynolds number range and flap configuration.
Author: G. Chester Furlong
Author: G. Chester Furlong
Author: John R. Spreiter
Author: John R. Spreiter
Author: John R. Spreiter
Author: James M. Nissen
Author: 
Author: G. Chester Furlong
Author: John H. Quinn
Author: O. E. Sipe (Jr.)
Author: James E. Fitzpatrick