A Tabulation Of Wind Tunnel Pressure Data And Section Aerodynamic Characteristics At Mach Numbers Of 161 And 201 For A Reflex Cambered Wing And A Cambered And Twisted Wing Having The Same Swept Planform
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Author | : Emma Jean Landrum |
Publisher | : |
Total Pages | : 70 |
Release | : 1962 |
Genre | : |
ISBN | : |
Download A Tabulation of Wind-tunnel Pressure Data and Section Aerodynamic Characteristics at Mach Numbers of 1.61 and 2.01 for a Reflex Cambered Wing and a Cambered and Twisted Wing Having the Same Swept Planform Book in PDF, Epub and Kindle
Author | : Emma Jean Landrum |
Publisher | : |
Total Pages | : 76 |
Release | : 1962 |
Genre | : Aerofoils |
ISBN | : |
Download A Tabulation of Wind-tunnel Pressure Data and Section Aerodynamic Characteristics at Mach Numbers of 1.61 and 2.01 for a Reflex Cambered Wing and a Cambered and Twisted Wing Having the Same Swept Planform Book in PDF, Epub and Kindle
Author | : Frederick Cyril Grant |
Publisher | : |
Total Pages | : 196 |
Release | : 1958 |
Genre | : Airplanes |
ISBN | : |
Download A Tabulation of Wind-tunnel Pressure Data at Mach Numbers of 1.61 and 2.01 of Five Swept Wings of the Same Plan Form But Different Surface Shapes Book in PDF, Epub and Kindle
Author | : Emma Jean Landrum |
Publisher | : |
Total Pages | : 40 |
Release | : 1962 |
Genre | : Airplanes |
ISBN | : |
Download A Tabulation of Section Aerodynamic Characteristics at Mach Numbers of 1.61 and 2.01 for Four Swept Wings Having the Same Planform But Different Surface Shapes Book in PDF, Epub and Kindle
Author | : |
Publisher | : |
Total Pages | : 36 |
Release | : 1965 |
Genre | : |
ISBN | : |
Download Longitudinal and Lateral Aerodynamic Characteristics at Mach Numbers from 0.60 to 4.63 for Two Variable-sweep Configurations Book in PDF, Epub and Kindle
Author | : Patrick A. Gainer |
Publisher | : |
Total Pages | : 40 |
Release | : 1961 |
Genre | : Aerodynamics |
ISBN | : |
Download A Method of Determining Aerodynamic-influence Coefficients from Wind-tunnel Data for Wings at Supersonic Speeds Book in PDF, Epub and Kindle
Author | : A. Warner Robins |
Publisher | : |
Total Pages | : 68 |
Release | : 1979 |
Genre | : Hypersonic planes |
ISBN | : |
Download Aerodynamic Characteristics at Mach Numbers of 1.5, 1.8, and 2.0 of a Blended Wing-body Configuration with and Without Integral Canards Book in PDF, Epub and Kindle
Author | : |
Publisher | : |
Total Pages | : 41 |
Release | : 1962 |
Genre | : |
ISBN | : |
Download A TABULATION OF SECTION AERODYNAMIC CHARACTERISTICS AT MACH NUMBERS OF 1.61 AND 2.01 FOR FOUR SWEPT WINGS HAVING THE SAME PLATFORM BUT DIFFERENT SURFACE SHAPES. Book in PDF, Epub and Kindle
The section normal-force and pitching-moment coefficients for four sweepback wings with different surface shapes are tabulated. All the wings had NACA 65A005 thickness distributions, 50 degrees of sweepback at the quarter chord, a taper ratio of 0.20, and an aspect ratio of 3.5. There were three twisted wings and one flat wing. The twisted wings had 6 degrees of washout at the tip, but the twist variation along the span was either linear, quadratic, or cubic. The wings were tested at Mach numbers of 1.61 and 2.01 with fixed and free transition through a Reynolds number range of 1.7 to 3.6 x 10 to the 6th power. Angle-of-attack range was from -20 to 20 degrees.
Author | : Emma Jean Landrum |
Publisher | : |
Total Pages | : 36 |
Release | : 1962 |
Genre | : |
ISBN | : |
Download A Tabulation of Section Aerodynamic Characteristics at Mach Numbers of 1.61 and 2.01 for Four Swept Wings Having the Same Planform But Different Surface Shapes Book in PDF, Epub and Kindle
Author | : Marlowe D. Cassetti |
Publisher | : |
Total Pages | : 104 |
Release | : 1961 |
Genre | : Transonic wind tunnels |
ISBN | : |
Download Transonic Aerodynamic Loading Characteristics of a Wing-body-tail Combination Having 52.5° Sweptback Wing of Aspect Ratio 3 with Conical Wing Camber and Body Indentation for a Design Mach Number [square Root Of] 2 Book in PDF, Epub and Kindle
An investigation has been made of the effects of conical wing camber and body indentation according to the supersonic area rule on the aerodynamic wing loading characteristics of a wing-body-tail configuration at transonic speeds. The wing aspect ratio was 3, taper ratio was 0.1, and quarter-chord-line sweepback was 52.5° with 3-percent-thick airfoil sections. The tests were conducted in the Langley 16-foot transonic tunnel at Mach numbers from 0.80 to 1.05 and at angles of attack from 0° to 14°, with Reynolds numbers based on mean aerodynamic chord varying from 7 x 106 to 8 x 106. Conical camber delayed wing-tip stall and reduced the severity of the accompanying longitudinal instability but did not appreciably affect the spanwise load distribution at angles of attack below tip stall. Body indentation reduced to transonic chordwise center-of-pressure travel from about 8 percent to 5 percent of the mean aerodynamic chord.