Pitot Pressure Measurements In Flow Fields Behind A Rectangular Nozzle With Exhaust Jet For Free Stream Mach Numbers Of 000 060 And 120
Download Pitot Pressure Measurements In Flow Fields Behind A Rectangular Nozzle With Exhaust Jet For Free Stream Mach Numbers Of 000 060 And 120 full books in PDF, epub, and Kindle. Read online free Pitot Pressure Measurements In Flow Fields Behind A Rectangular Nozzle With Exhaust Jet For Free Stream Mach Numbers Of 000 060 And 120 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Author | : |
Publisher | : |
Total Pages | : 160 |
Release | : 1986 |
Genre | : |
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Download Pilot-pressure Measurements in Flow Fields Behind a Rectangular Nozzle with Exhaust Jet for Free-stream Mach Numbers of 0.00, 0.60, and 1.20 Book in PDF, Epub and Kindle
Author | : Lawrence Elwood Putnam |
Publisher | : |
Total Pages | : 160 |
Release | : 1986 |
Genre | : Aircraft exhaust emissions |
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Download Pitot-pressure Measurements in Flow Fields Behind a Rectangular Nozzle with Exhaust Jet for Free-stream Mach Numbers of 0.00, 0.60, and 1.20 Book in PDF, Epub and Kindle
Author | : Frank J. Centolanzi |
Publisher | : |
Total Pages | : 82 |
Release | : 1959 |
Genre | : Mach number |
ISBN | : |
Download Measured and Theoretical Flow Fields Behind a Rectangular and a Triangular Wing Up to High Angles of Attack at a Mach Number of 2.46 Book in PDF, Epub and Kindle
Author | : Norman R. Richardson |
Publisher | : |
Total Pages | : 30 |
Release | : 1959 |
Genre | : Mach number |
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Download Wind-tunnel Calibrations of a Combined Pitot-static Tube Vane-type Flow-direction Transmitter, and Stagnation-temperature Element at Mach Numbers from 0.60 to 2.87 Book in PDF, Epub and Kindle
Author | : W. F. Lindsey |
Publisher | : |
Total Pages | : 20 |
Release | : 1944 |
Genre | : Aerodynamics |
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Download Effect of Mach Number on Position Error as Applied to a Pitot-static Tube Located 0.55 Chord Ahead of an Airplane Wing Book in PDF, Epub and Kindle
Summary: The effect on static-pressure measurements of locating a pitot-static tube 0.55 chord ahead of an airfoil section has been investigated. The tests were conducted in the NACA 24-inch high-speed tunnel on airfoil sections of various thickness ratios over a large range of Mach number. The results show that for a wing having a thickness ratio of 0.15 the measured Mach number, determined from a pitot-static-tube reading, is approximately 0.01 too low at a stream Mach number of 0.4 and approximately 0.03 too low at a Mach number of 0.8.
Author | : Frank J. Centolanzi |
Publisher | : |
Total Pages | : 0 |
Release | : 1959 |
Genre | : Mach number |
ISBN | : |
Download Measured and Theoretical Flow Fields Behind a Rectangular and a Triangular Wing Up to High Angles of Attack at a Mach Number of 2.46 Book in PDF, Epub and Kindle
Author | : Lana M. Couch |
Publisher | : |
Total Pages | : 146 |
Release | : 1969 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Download Flow-field Measurements Downstream of Two Protuberances on a Flat Plate Submerged in a Turbulent Boundary Layer at Mach 2.49 and 4.44 Book in PDF, Epub and Kindle
Author | : George H. Holdaway |
Publisher | : |
Total Pages | : 62 |
Release | : 1964 |
Genre | : Aerodynamic load |
ISBN | : |
Download Flow Field and Surface Pressures on a Blunt Half-cone Entry Configuration at Mach Numbers of 7.4 and 10.4 Book in PDF, Epub and Kindle
Author | : Francis J. Capone |
Publisher | : |
Total Pages | : 36 |
Release | : 1961 |
Genre | : |
ISBN | : |
Download Wind-tunnel Tests of Seven Static-pressure Probes at Transonic Speeds Book in PDF, Epub and Kindle
Wind-tunnel tests have been conducted to determine the errors of 3 seven static-pressure probes mounted very close to the nose of a body of revolution simulating a missile forebody. The tests were conducted at Mach numbers from 0.80 to 1.08 and at angles of attack from -1.7° to 8.4°. The test Reynolds number per foot varied from 3.35 x 106 to 4.05 x 106. For three 4-vane, gimbaled probes, the static-pressure errors remained constant throughout the test angle-of-attack range for all Mach numbers except 1.02. For two single-vane, self-rotating probes having two orifices at ±37.5° from the plane of symmetry on the lower surface of the probe body, the static-pressure error varied as much as 1.5 percent of free-stream static pressure through the test angle-of-attack range for all Mach numbers. For two fixed, cone-cylinder probes of short length and large diameter, the static-pressure error varied over the test angle-of-attack range at constant Mach numbers as much as 8 to 10 percent of free-stream static pressure.
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