Download or read book 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 written by G. Chester Furlong and published by . This book was released on 1950 with total page 43 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects 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 written by G. Chester Furlong and published by . This book was released on 1950 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects 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 written by G Chester Furlong and published by . This book was released on 1950 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects 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 written by and published by . This book was released on 1952 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book 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 written by James E. Fitzpatrick and published by . This book was released on 1952 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects 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 written by James E. Fitzpatrick and published by . This book was released on 1952 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Summary of Low Speed Airfoil Data written by Michael S. Selig and published by Soartech. This book was released on 1995 with total page 320 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerospace Vehicle Design Aircraft design written by Karl Dawson Wood and published by . This book was released on 1968 with total page 504 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics of the NACA 747A315 and 747A415 Airfoils from Tests in the NACA Two dimensional Low turbulence Pressure Tunnel written by Albert E. Von Doenhoff and published by . This book was released on 1944 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: Two low-drag airfoils, the NACA 747A315 and the NACA 747A415, designed to have reduced pitching moments about the quarter-chord point and moderately high values of the design lift coefficient have been tested in the NACA two-dimensional low-turbulence pressure tunnel. Section lift, drag, and pitching-moment coefficients are presented for Reynolds numbers of 3 x 106, 6 x 106, and 9 x 106, together with section lift and section drag data for a Reynolds number of 6 x 106 for the same airfoils with roughened leading edges.
Download or read book Aerofoil Sections written by Friedrich Wilhelm Riegels and published by . This book was released on 1961 with total page 281 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2 0 written by Robert S. Osborne and published by . This book was released on 1960 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of a Lower Surface Jet on the Lift drag Ratio of a 45 Sweptback Wing at a Mach Number of 2 01 written by Emma Jean Landrum and published by . This book was released on 1960 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book 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 written by Emma Jean Landrum and published by . This book was released on 1961 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effect of Mach and Reynolds Numbers on the Maximum Lift Coefficient Obtainable in Gradual and Abrupt Stalls of a Pursuit Airplane Equipped with a Low drag Wing written by John R. Spreiter and published by . This book was released on 1945 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Effect of Mach and Reynolds Numbers on Maximum Lift Coefficients written by John R. Spreiter and published by . This book was released on 1946 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book A Effects of Reynolds Number and Leading edge Roughness on Lift and Drag Characteristics of the NACA 653 418 written by John H. Quinn and published by . This book was released on 1945 with total page 7 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were made in the Langley two-dimensional low-turbulence tunnels of an NACA 653-418, a = 1.0 airfoil section with roughness in the form of carborundum grains applied to the leading edge. Roughness grains having average diameters of 0.0003 and 0.0007 airfoil chord were applied to the leading edge of the wing, and lift and drag measurements were made for a range of Reynolds numbers from 0.23 to 3.0 x 106. From a comparison of data obtained in the present tests with data obtained in tests of the smooth wing, marked reductions in maximum lift coefficient were found to be caused by the roughness throughout the test range of Reynolds number. The drag coefficient at the design lift coefficient increased sharply and the lift-curve slope decreased rapidly at a critical Reynolds number that depended upon the size of the carborundum grains. This critical Reynolds number occurred at approximately 0.50 and 0.70 x 106 for the 0.0003- and the 0.0007-chord-diameter roughness grains, respectively. With roughness, a decrease in maximum lift coefficient as great as 0.2, a decrease in lift-curve slope of 0.028, and an increase in drag coefficient at the design lift coefficient of 0.0007 were observed at a Reynolds number of 1.0 x 106. For the smooth wing at the same Reynolds number, the maximum lift coefficient was 1.19, the lift-curve slope was 0.116, and the drag coefficient was 0.0077. At Reynolds numbers greater than 1.0 x 106, the scale effect on the lift and drag characteristics of the section with both degrees of roughness was generally in the same direction as the effect on the lift and drag characteristics of the smooth airfoil.
Download or read book Effects of Wing Planform on the Aerodynamic Characteristics of a Wing body tail Model at Mach Numbers 3 96 and 4 63 written by Maurice O. Feryn and published by . This book was released on 1966 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
