Author: G. Chester FurlongPublisher:
ISBN:
Category :
Languages : en
Pages : 43
Book Description
Effects of Mach Number Up to 0.34 and Reynolds Number Up to 8 X 10 6 on the Maximum Lift Coefficient of a Wing of NACA 66-series Airfoil Sections
Author: G. Chester FurlongEffects of Mach Number Up to 0.34 and Reynolds Number Up to 8 X 10(exp 6) on the Maximum Lift Coefficient of a Wing of NACA 66-Series Airfoil Sections
Author: G. Chester FurlongEffects of Mach Number Up to 0.34 and Reynolds Number Up to 8 X 10 to the 6th Power on the Maximum Lift Coefficient of a Wing of NACA 66-series Airfoil Sections
Author: G Chester FurlongEffects of Mach Number Variation Between 0.07 and 0.34 and Reynolds Number Variation Between 0.97 X 10(exp 6) and 8.1 X 10(exp 6) on the Maximum Lift Coefficient of a Wing of NACA 64-210 Airfoil Sections
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.
Effects of Mach Number Variation Between 0.07 and 0.34 and Reynolds Number Variation Between 0.97 X 10 6 and 8.10 X 10 6 on the Maximum Lift Coefficient of a Wing of NACA 64-210 Airfoil Sections
Author: James E. FitzpatrickEffects of Mach Number Variation Between 0.07 and 0.34 and Reynolds Number Variation Between 970,000 and 8,100,000 on the Maximum Lift Coefficient of a Wing of NACA 64-210 Airfoil Sections
Author: James E. FitzpatrickPublisher:
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.
A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0
Author: Robert S. OsbornePublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 20
Book Description
Effects of a Lower Surface Jet on the Lift-drag Ratio of a 45° Sweptback Wing at a Mach Number of 2.01
Author: Emma Jean LandrumPublisher:
ISBN:
Category : Mach number
Languages : en
Pages : 44
Book Description
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
Author: Emma Jean LandrumPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 52
Book Description
Effect of Mach and Reynolds Numbers on Maximum Lift Coefficients
Author: John R. SpreiterPublisher:
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.