Download or read book Boundary layer Characteristics at Mach Numbers 2 Through 5 in the Test Section of the 12 inch Supersonic Tunnel written by D. R. Bell and published by . This book was released on 1963 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: As part of a general tunnel calibration program, an investigation was made of the boundary-layer characteristics at Mach numbers 2, 3, 4, and 5 in the test section of the 12-Inch Supersonic Tunnel (D). The boundary-layer measurements were made at one longitudinal station (near the pitch sector center of rotation) on the centerline of both the flexible plate and sidewall. Measurements were also made at vertical locations on the sidewall between the sidewall centerline and the upper flexible plate. The boundary-layer total thickness, displacement thickness, and momentum thickness, are presented at each Mach number over a Reynolds number range corresponding, in general, to tunnel stagnation pressures between 5 and 60 psia. At each Mach number, the variation of displacement thickness on the side wall between the centerline and the upper flexible plate is presented as is a correlation of the flexible plate displacement thickness with experimental data obtained in other wind tunnels. Velocity profiles and test section Mach numbers are presented to indicate variations with Reynolds number.
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Note written by and published by . This book was released on 1971 with total page 612 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book U S Government Research Reports written by and published by . This book was released on 1964 with total page 2180 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Power law Velocity profile exponent Variations with Reynolds Number Wall Cooling and Mach Number in a Turbulent Boundary Layer written by Charles Borden Johnson and published by . This book was released on 1969 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Investigation of the Boundary layer Characteristics in the Test Section of a 40 by 40 inch Supersonic Tunnel written by Jerry Jones and published by . This book was released on 1960 with total page 23 pages. Available in PDF, EPUB and Kindle. Book excerpt: A test program was conducted to investigate the boundary-layer characteristics of the von Karman Gas Dynamics Facility's 40 x 40 inch continuous, supersonic wind tunnel (Tunnel A). The program was divided into two parts: (1) a survery of the boundary layer at one station at the center of the flexible nozzle plate (curved wall) and (2) a survey at one station at the center of the tunnel sidewall. For the minimum Reynolds number, the boundary-layer displacement thickness is greater on the sidewall than on the flexible nozzle plate at all Mach numbers, whereas at maximum Reynolds numbers the displacement thicknesses are essentially the same. The measured displacement thicknesses on the flexible nozzle plate and sidewall showed good agreement with theory when the turbulent skin friction coefficients were evaluated from Reynolds numbers based on wall density and kinematic viscosity. Theoretical estimates of the displacement thicknesses determined by using Reynolds numbers based on free-stream density and kinematic viscosity were consistently higher than the experimental values.
Download or read book Flow Characteristics of a 12 in Intermittent Supersonic Tunnel written by A. Anderson and published by . This book was released on 1963 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: A compilation has been made of all calibration data obtained since 1958 in the von Karman Gas Dynamics Facility's 12-Inch Supersonic Tunnel (D). Test section flow characteristics are presented for the nominal Mach number range from 1.5 to 5 over the available Reynolds number range. Along the axis of the test section for all contours the maximum variation in Mach number is within =0.01, and the average flow angles in pitch and yaw are less than 0.2 deg. Somewhat larger variations in Mach number and flow angularity are found off-axis. At the higher Mach numbers, significant changes in the average test section Mach number with decreasing Reynolds number are accompanied by corresponding changes in the tunnel boundary layer. (Author).
Download or read book Technical Abstract Bulletin written by and published by . This book was released on with total page 912 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Paper written by and published by . This book was released on 1987 with total page 744 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Index to NASA Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1960-07 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Summary of Information on Support Interference at Transonic and Supersonic Speeds written by Eugene S. Love and published by . This book was released on 1954 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: A compilation of available information on the problem of support interference at transonic and supersonic speeds is presented.
Download or read book NASA Scientific and Technical Publications written by and published by . This book was released on 1993 with total page 134 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Research Review written by and published by . This book was released on 1970-03 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Research Review written by United States. Air Force. Office of Aerospace Research and published by . This book was released on 1969 with total page 346 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Dominance of Radiated Aerodynamic Noise on Boundary layer Transition in Supersonic hypersonic Wind Tunnels written by Samuel R. Pate and published by . This book was released on 1978 with total page 418 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted to determine the effects of radiated aerodynamic-noise on boundary-layer transition in supersonic-hypersonic wind tunnels. It is conclusively shown that the aerodynamic noise (pressure fluctuations associated with sound waves), which radiate from the tunnel wall, turbulent boundary layer, will dominate the transition process on sharp flat places and sharp slender cones at zero incidence.
Download or read book Boundary layer Transition Correlation on a Slender Cone in Wind Tunnels and Flight for Indications of Flow Quality written by N. Sam Dougherty and published by . This book was released on 1982 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: Boundary-layer transition location measurements were made on a 10-deg sharp cone in 23 wind tunnels in the United States and Europe and in flight. The data were acquired at subsonic, transonic, and supersonic Mach numbers over a range of unit Reynolds numbers in an effort to obtain an improved understanding of the effect of wind tunnel flow quality on transition location. The data indicate that the transition mechanism in both wind tunnels and flight is associated with the formation of Tollmien-Schlichting waves in the laminar boundary layer. However, the location of the end of transition was found to be primarily a function of the noise under the laminar boundary of the cone surface and, within + or - 20 percent, independent of Mach number and unit Reynolds number. (Author).
Download or read book NASA Scientific and Technical Reports written by United States. National Aeronautics and Space Administration Scientific and Technical Information Division and published by . This book was released on 1967 with total page 2300 pages. Available in PDF, EPUB and Kindle. Book excerpt:
