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Base-Pressure Measurements with Wire-Supported Models at Supersonic Speeds
Report Number: AEDC TN 61-23
Author(s): J. Don Gray
Corporate Author: VKF, ARO, Inc.
Publication Date: 5/1/1961
Pages: 24
Contract: AF 40(600)-800
Project: 8952
Task: None Given
AD Number: AD0252548
Photo Enhancement: Incomplete
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A Forced-Oscillation Balance System for the von Kármán Facility 40- by 40-Inch Supersonic Tunnel
Report Number: AEDC TN 61-63
Author(s): C. J. Welsh, Q. P. Hance, and L. K. Ward
Corporate Author: VKF, ARO, Inc.
Publication Date: 5/1/1961
Pages: 19
Contract: AF 40(600)-800
Project: 8952
Task: None Given
AD Number: AD0257380
Photo Enhancement: Incomplete
Abstract Text:
A description of a recently developed, forcedoscillation balance system for the von Karman Gas Dynamics Facility's 40- by 40-inch supersonic wind tunnel is given. Measured damping-inpitch derivatives for a flared afterbody reentry shape at free stream Mach number 4 over a Reynolds number range from 0.37 x 10 to the 6th power to 0.58 x 10 to the 6th power based on body diameter are presented.
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Investigation of Boundary-Layer Suction on a 20-Caliber Orgive Cylinder at Mach Numbers 2.5, 3.0, 3.5, and 4.0
Report Number: AEDC TN 61-66
Author(s): W. T. Strike and S. Pate
Corporate Author: VKF, ARO, Inc.
Publication Date: 6/1/1961
Pages: 30
Contract: AF 40(600)-800
Project: 1366
Task: 14080
AD Number: AD0257381
Photo Enhancement: Incomplete
Abstract Text:
A second investigation was conducted in the 12in., intermittent, supersonic wind tunnel of the von Karman Gas Dynamics Facility to measure the effectiveness of boundary-layer suction on a 20 caliber ogive cylinder. The application of suction type boundary-layer control on the ogive was investigated at Mach numbers 2.5, 3.0, 3.5, and 4.0 over a unit Reynolds number range from 0. 07 to 1.03 x 10 to the 6th power per inch with the model at zero angle of attack. Some additional data were obtained at 2-deg angle of attack at Mach number 3. As a result of improving the design of the suction system a significant gain was made in reducing the net drag of the model at Mach number 3 by boundary-layer suction. The presence of the suction slots with no suction when compared with the sealed slot configuration (that is, smooth model) had some influence on the boundary-layer characteristics at all Mach numbers.
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Pressure Distribution and Shock Shape Over Blunted Slender Cones at Mach Numbers From 16 to 19
Report Number: AEDC TN 61-81
Author(s): Clark H. Lewis
Corporate Author: VKF, ARO, Inc.
Publication Date: 8/1/1961
Pages: 21
Contract: AF 40(600)-800
Project: 8951
Task: 89103
AD Number: AD0261846
Photo Enhancement: Incomplete
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Description and Preliminary Calibration of a Low-Density, Hypervelocity Wind Tunnel
Report Number: AEDC TN 61-83
Author(s): J. Leith Potter, Max Kinslow, George D. Arnery, Jr., and Allan B. Bailey
Corporate Author: VKF, ARO, Inc.
Publication Date: 8/1/1961
Pages: 49
Contract: AF 40(600)-800
Project: 8950
Task: 89602
AD Number: AD0262466
Photo Enhancement: Incomplete
Abstract Text:
A small, low-density, hypervelocity, continuous wind tunnel operating at total temperatures from 2000 to 4000 K is described, and initial experiments designed to determine the characteristics of the flow are discussed. Effects of low Reynolds numbers on impact-pressure probes and static-pressure probes are shown. Preliminary work with a probe for measuring local mass-flow rate is outlined, and results are shown to be in agreement with impact and static pressure measurements. Axial and transverse surveys of flow in the nozzle are presented to illustrate the extent of boundary-layer growth and the useable core of flow. A diffuser is proved to be advantageous, even though very low Reynolds numbers are typical of the tunnel. A comparison of data on drag of spheres, including measurements from the new wind tunnel, is presented.
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Pressure Distributions on a Hemisphere Cylinder at Supersonic and Hypersonic Mach Numbers
Report Number: AEDC TN 61-96
Author(s): A. L. Baer
Corporate Author: VKF, ARO, Inc.
Publication Date: 8/1/1961
Pages: 34
Contract: AF 40(600)-800
Project: None Given
Task: None Given
AD Number: AD0261501
Photo Enhancement: Incomplete
Abstract Text:
Pressure distribution tests at supersonic and hypersonic speeds were conducted in the von Karman Gas Dynamics Facility (VKF), Arnold Center, Air Force Systems Command on AGARD Model E, a hemisphere cylinder configuration. Various experimental data concerning the aerodynamic characteristics of blunt nosed bodies are available; however, relatively few sources present findings over a wide arch number range. The present investigations, stimulated by the need for applicable experimental data to compare with the predictions of various theories, were conducted a Mach numbers 2 through 8 over a Reynolds number range from 0.17 x 10 to the 6th power to 0.51 x 10 to the 6th power per inch. A comparison is made of experimental results with available theoretical predictions of pressure distributions, pressure drag, shock wave shapes, and bow shock wave detachment distances.
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Tables of Thermodynamic Properties of Air From 90 to 1500 Degrees K
Report Number: AEDC TN 61-103
Author(s): R. L. Humphrey and C.A. Neel
Corporate Author: VKF and Scientific Computing Services ARO, Inc.
Publication Date: 8/1/1961
Pages: 112
Contract: AF 40(600)-800
Project: None Given
Task: None Given
AD Number: AD0262692
Photo Enhancement: Not Needed
Abstract Text:
Tables are presented for the thermodynamic properties of air from 90 to 1500 K using (1) temperature and pressure and (2) temperature and density as independent variables. The pressure tables range from 1 to 1200 atmospheres, whereas the density tables extend from 10 to the -7th power to 400 relative atmospheres (or amagat units). The tabulated properties are the compressibility factor Z, the dimensionless functions E/RT, H/RT and S/R, together with pressure and density. The tables account for the so-called real gas effects (van der Waals' effects) at high pressures, but do not include the effects of the small amounts of dissociation at low pressures and high temperatures. The sources for the tables as well as the final tables are discussed.
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Packaging of a Hypervelocity Radio Telemeter to Withstand High Impulse Accelerations
Report Number: AEDC TN 61-119
Author(s): Raymond Young
Corporate Author: VKF, ARO, Inc.
Publication Date: 10/1/1961
Pages: 34
Contract: AF 40(600)-800
Project: 8952
Task: 89511
AD Number: AD0264688
Photo Enhancement: Incomplete
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