A Tabulation Of Wind Tunnel Pressure Data At Mach Numbers Of 161 And 201 Of Five Swept Wings Of The Same Plan Form But Different Surface Shapes
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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 | : 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 | : 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 | : Robert E. Dannenberg |
Publisher | : |
Total Pages | : 678 |
Release | : 1950 |
Genre | : Aerodynamic load |
ISBN | : |
Download Measurements of Section Characteristics of a 45 Degree Swept Wing Spanning a Rectangular Low-speed Wind Tunnel as Affected by the Tunnel Walls Book in PDF, Epub and Kindle
Tunnel-wall corrections for the induced upwash velocity for a swept wing completely spanning a rectangular wind tunnel are included in the appendix.
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 | : S. Katzoff |
Publisher | : |
Total Pages | : 670 |
Release | : 1948 |
Genre | : Airplanes |
ISBN | : |
Download Calculation of Tunnel-induced Upwash Velocities for Swept and Yawed Wings Book in PDF, Epub and Kindle
The tunnel-induced upwash for a wing of any plan form and load distribution in a rectangular tunnel may be found with the aid of only two charts. One is given in the present paper. The second must be computed for each tunnel. The second chart is given for an open tunnel of 2:1 width-height ratio, a closed tunnel of 2:5 width-height ratio, and a closed tunnel of 10:7 width-height ratio.
Author | : Raymond E. Mineck |
Publisher | : |
Total Pages | : 88 |
Release | : 1993 |
Genre | : |
ISBN | : |
Download Wind-tunnel Investigation of Aerodynamic Efficiency of Three Planar Elliptical Wings with Curvature of Quarter-chord Line Book in PDF, Epub and Kindle
Author | : Harold Mirels |
Publisher | : |
Total Pages | : 28 |
Release | : 1949 |
Genre | : Aerodynamic load |
ISBN | : |
Download Experimental Pressure Distributions Over Wing Tips at Mach Number 1.9 Book in PDF, Epub and Kindle
An investigation was conducted at a Mach number of 1.90 to determine spanwise pressure distribution over a wing tip in a region influenced by a sharp subsonic trailing edge. The wing section was a symmetrical wedge of 5 degrees 43 minutes total included angle in the free-stream direction. The investigation was conducted over a range of angles of attack from -10 to 10 degrees at a Reynolds number of 3,400,000 per foot.
Author | : Julio Chu |
Publisher | : |
Total Pages | : 38 |
Release | : 1996 |
Genre | : Angle of attack |
ISBN | : |
Download Experimental Surface Pressure Data Obtained on 65 ̊delta Wing Across Reynolds Number and Mach Number Ranges Book in PDF, Epub and Kindle