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Comparison of Hotshot Tunnel Force, Pressure, Heat-Transfer and Shock Shape Data with Shock Tunnel Data
Report Number: AEDC TDR 64-1
Author(s): E. E. Edenfield
Corporate Author: ARO, Inc.
Publication Date: 1/1/1964
Pages: 25
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0428916
Photo Enhancement: Incomplete
Abstract Text:
Comparison is made of force, pressure, heattransfer, and shock shape data from tests in the AEDC-VKF hotshot tunnels and in the Cornell Aeronautical Laboratory 48 Inch Shock Tunnel. Several cone models of varying bluntness were tested through an angle-of-attack range of 0 to 40 deg at each facility. Excellent agreement of the hotshot and the shock tunnel data is shown.
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Theoretical Base Pressure Analysis of Axisymmetric Ejectors Without Induced Flow
Report Number: AEDC TDR 64-3
Author(s): R. C. Bauer
Corporate Author: ARO, Inc.
Laboratory: Arnold Engineering Development Center
Publication Date: 1/1/1964
Pages: 50
Contract: AF 40(600)-1000
Project: 6950
Task: 695002
AD Number: AD0428533
Photo Enhancement: Not Needed
Abstract Text:
The two-dimensional supersonic base pressure theory developed by Dr. H. H. Korst, which applies to two-dimensional systems with straight jet boundaries, has been modified to be more applicable to axisymmetric ejector systems. The modification consists of a new theory for estimating the peak recompression static pressure which is applicable to either axisymmetric or two-dimensional jets having straight or curved boundaries. Significantly, the recompression mechanism is not independent of viscous effects for systems which produce a non-uniform inviscid flow field. Both the recompression theory and the modified base pressure theory are experimentally verified for the case of isoenergetic mixing and negligible initial boundary layer. The recompression theory is shown to agree with experimental results to within =10% whereas the experimental base pressure results have a standard deviation of 6% with respect to the modified base pressure theory.
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Investigation of Flow Separation on a Two-Dimensional Flat Plate Having a Variable-Span Trailing-Edge Flap at M = 3 and 5
Report Number: AEDC TDR 64-14
Author(s): S. R. Pate
Corporate Author: ARO, Inc.
Publication Date: 3/1/1964
Pages: 34
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0432831
Photo Enhancement: Incomplete
Abstract Text:
An experimental investigation of separated boundary-layer flow was conducted on a two-dimensional flat plate having a variable-span trailingedge flap in the 12-in. Supersonic Tunnel (D) of the von Karman Gas Dynamics Facility. The tests were made at Mach numers 3 and 5 at zero angle of attack and over a Reynolds number range (based on plate length) from 0.26 to 16.7 x 10 to the 6th power. Model surface pressure distributions, schlieren photographs, and velocity distributions are presented. The effects of unit Reynolds number, plate length, flap span, and flap deflection angle on the separated region are investigated, and comparisons are made with existing theory.
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Heat-Transfer and Shadowgraph Tests of Several Elliptical Lifting Bodies at Mach 10
Report Number: AEDC TDR 64-19
Author(s): M. E. Hillsamer and J. P. Rhudy
Corporate Author: ARO, Inc.
Publication Date: 2/1/1964
Pages: 44
Contract: AF 40(600)-1000
Project: 1366
Task: 136607
AD Number: AD0429931
Photo Enhancement: Incomplete
Abstract Text:
Heat transfer and shadowgraph tests were conducted on several lifting bodies of elliptical cross section and sharp- and blunt-nose shapes to determine heat-transfer distributions and shock wave shapes around the various configurations. The tests were conducted at a nominal Mach number of 10 and free-stream unit Reynolds numbers of 0.31, 1.00, and 2.38 million per foot over an angle-of-attack range from 0 to 60 deg. Selected results of the tests presented in this report indicate slight increases in heat-transfer coefficient caused by increased Reynolds number and nose bluntness. Regions of flow separation are also shown on the leeward side of the models at pitch angles of 15 deg. and above.
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Equations and Charts for the Evaluation of the Hypersonic Aerodynamic Characteristics of Lifting Configurations by the Newtonian Theory
Report Number: AEDC TDR 64-25
Author(s): E. L. Clark and L. L. Trimmer
Corporate Author: ARO, Inc.
Publication Date: 3/1/1964
Pages: 82
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD431848
Photo Enhancement: Not Needed
Abstract Text:
The pressure distribution predicted by the modified Newtonian theory is used to develop equations for the aerodynamic forces, moments, and stability derivatives for components of hypersonic lifting configurations. In conjunction with the equations, a set of charts is presented to enable simple determination of the aerodynamic characteristics of swept cylinders, swept wedges, spherical segments, and cone frustums at zero sideslip and angles of attack from 0 to 180 degrees. This method allows evaluation of most delta wing-body combinations without the need for numerical or graphical integration. As an example of the procedure, the theoretical characteristics of a blunt 75-degree swept delta wing are calculated and compared with experimental results.
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Force and Pressure Tests of an Agard Calibration Model B at a Mach Number of 10
Report Number: AEDC TDR 64-31
Author(s): R. K. Matthews and L. L. Trimmer
Corporate Author: ARO, Inc.
Publication Date: 2/1/1964
Pages: 28
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0430701
Photo Enhancement: Not Needed
Abstract Text:
The AGARD Calibration Model B, with and without wings, was tested at a nominal Mach number of 10. Force and moment coefficients were obtained over a range of pitch and yaw angles from -5 to 15.5 degrees with a Reynolds number range from 1.10 x 10 to the 6th power to 9.80 x 10 to the 6th power, based on model length. The lift-curve slope, aerodynamic center, and drag coefficients show excellent correlation with data from other tunnels at various Mach numbers.
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Condensation in Hotshot Tunnels
Report Number: AEDC TDR 64-35
Author(s): B. J. Griffith, H. E. Deskins, and H. R. Little
Corporate Author: ARO, Inc.
Publication Date: 2/1/1964
Pages: 20
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0431046
Photo Enhancement: Incomplete
Abstract Text:
Tests have been conducted to determine the effects of condensation of nitrogen in the AEDC Hotshot Tunnels H and F. Free-stream static pressure was determined by an extrapolation of sharp flat-plate pressure data and an analysis of the nozzle static pressures. It is shown that the amount of supersaturation that can be achieved at high Mach numbers in air can also be obtained using nitrogen as the test gas.
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Specific Heat and Speed of Sound Data for Imperfect Air
Report Number: AEDC TDR 64-36
Author(s): Clark H. Lewis and Charles A. Neel
Corporate Author: ARO, Inc.
Publication Date: 4/1/1964
Pages: 150
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0600469
Photo Enhancement: Not Needed
Abstract Text:
Specific heat and speed of sound data were computed for imperfect air. The thermodynamic data included the effects of two-body intermolecular forces, and the results were obtained by numerical interpolation and differentiation of the recent data of Hilsenrath and Klein (AD-416 040). Comparisons with previous perfect gas calculations showed small effects in the isentropic exponent gamma sub E and dimensionless speed of sound a/a sub a below one amagat and negligible effects on the specific heat data for all densities up to log rho = 2.2.
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Charts of Normal Shock Wave Properties in Imperfect Air
Report Number: AEDC TDR 64-43
Author(s): Clark H. Lewis and E. G. Burgess, III
Corporate Author: ARO, Inc.
Publication Date: 3/1/1964
Pages: 46
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0433958
Photo Enhancement: Not Needed
Abstract Text:
Gas-dynamic properties which include the effects of dissociation, ionization, and intermolecular forces (van der Walls) are presented for incident and reflected shock waves in equilibrium imperfect air. Charts are presented for incident shock Mach numbers in the range from 6 to 30 into (ideal) air at a temperature of 300 K and pressures in the range from 10 to the minus 4 power to 10 to the 3rd power cm Hg. The temperature and density in any region do not exceed, respectively, 15,000 K and 158 amagats. In addition to the usual incident and reflected shock properties, stagnation conditions upstream and downstream and conditions immediately downstream of a standing shock wave are also presented. At pressures above one atmosphere in the undisturbed gas, the effects of the intermolecular forces on the gas-dynamic properties are demonstrated.
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An Experimental Study of Diffusers in an Open-Jet, Low-Density, Hypersonic Wind Tunnel
Report Number: AEDC TDR 64-47
Author(s): David E. Boylan
Corporate Author: ARO, Inc.
Publication Date: 4/1/1964
Pages: 61
Contract: AF 40(600)-1000
Project: 8950
Task: 895004
AD Number: AD0434380
Photo Enhancement: Incomplete
Abstract Text:
An experimental investigation of supersonic diffuser performance in a flow regime in which viscous and compressibility influences are equally important was conducted. The investigation involved Mach numbers from 6 to 16.5. It is shown that, although diffuser recovery compared to higher density regimes is small, using the proper diffuser allowed the required wind tunnel exhaust pressure to be up to 35 times the pressure existing in the test chamber. While this may not seem exceptional at first glance, it is important to note that this was achieved in conjunction with Reynolds numbers on the order of 10 to the minus 3 power below those typical of tunnels yielding higher recoveries.
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A Data Reduction Program for Hotshot Tunnels Based on the Fay-Riddell Heat-Transfer Rate Using Nitrogen at Stagnation Temperatures from 1500 to 5000 Degrees K
Report Number: AEDC TDR 64-50
Author(s): Martin Grabau, H. K. Smithson, Jr., and Wanda J. Little
Corporate Author: ARO, Inc.
Publication Date: 6/1/1964
Pages: 57
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0601070
Photo Enhancement: Not Needed
Abstract Text:
A method is set forth for the computation of test-section, aftershock, and stagnation conditions in hotshot tunnels of Arnold Engineering Development Center, using nitrogen at stagnation temperatures from 1500 to 5000 K. The basic input data are the stagnation pressure in the reservoir, the pitot pressure behind a normal shock, and the heat-transfer rate at the stagnation point. The value of the overall enthalpy is adjusted by numerical iteration until the measured and computed heat-transfer rates are numerically equal within a prescribed tolerance.
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Evaluation of Throat Materials in the Hotshot Tunnel F
Report Number: AEDC TDR 64-56
Author(s): H. K. Smithson
Corporate Author: ARO, Inc.
Publication Date: 3/1/1964
Pages: 11
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0433670
Photo Enhancement: Incomplete
Abstract Text:
Several experimental throat materials were tested in the 100-in. Tunnel F. Results of these tests showed that tungsten and copper-filled tungsten were more satisfactory than other materials investigated.
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Experimental Determination of Aerodynamic Drag on a Blunted 10-Deg Cone at Angles of Attack in Hypersonic, Rarefied Flow
Report Number: AEDC TDR 64-60
Author(s): David E. Boylan and William H. Sims
Corporate Author: ARO, Inc.
Publication Date: 4/1/1964
Pages: 28
Contract: AF 40(600)-1000
Project: 8953
Task: 895306
AD Number: AD0435860
Photo Enhancement: Incomplete
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Local Heat-Transfer Coefficients in a Nozzle with High-Speed Laminar Flow
Report Number: AEDC TDR 64-61
Author(s): William H. Carden
Corporate Author: ARO, Inc.
Publication Date: 4/1/1964
Pages: 34
Contract: AF 40(600)-1000
Project: 8950
Task: 895004
AD Number: AD0434369
Photo Enhancement: Incomplete
Abstract Text:
An experimental investigation of the local heattransfer coefficient in the throat region of a nozzle operating under conditions of cold wall, thick laminar boundary-layer, low-density, highspeed flow has been conducted. The experimental results have been compared with several analytic procedures for predicting the heat-transfer coefficient in laminar flow. The simple flat plate equation is shown to underestimate the heat-transfer coefficient, while the method of Cohen and Reshotko predicts coefficients which are too large. The incremental flat plate method of Pasqua and Stevens and a modification of a solution of Beckwith and Cohen exhibit good results downstream of the nozzle throat when reference to the value calculated by the simple flat plate equation at the nozzle exit. The effects of thermal raiation upstream of the nozzle throat are indicated.
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Tables of Thermodynamic Properties of Argon from 100 to 3000 Degrees K
Report Number: AEDC TDR 64-68
Author(s): Wanda J. Little
Corporate Author: ARO, Inc.
Laboratory: Arnold Engineering Development Center
Publication Date: 4/1/1964
Pages: 130
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0434368
Photo Enhancement: Not Needed
Abstract Text:
Tables of the thermodynamic properties of argon are presented for the temperature range of 100 to 3000 K. In the first table, temperature and pressure are the independent variables with the pressure range extending from one to 5000 atm. In the second table, temperature and density are the independent variables with a density range extending from 10 to the -7th to 630 amagats. The additional tabulated properties are the compressibility factor Z and the dimensionless functions E/RT, H/RT, and S/R. The sources of data and the tables are discussed.
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Charts of Normal Shock Wave Properties in Imperfect Nitrogen
Report Number: AEDC TDR 64-104
Author(s): Clark H. Lewis and E. G. Burgess, III
Corporate Author: ARO, Inc.
Publication Date: 5/1/1964
Pages: 46
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0600844
Photo Enhancement: Not Needed
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Flow Visualization Techniques for Use in Hypersonic Wind Tunnels
Report Number: AEDC TDR 64-108
Author(s): R. W. Rhudy
Corporate Author: ARO, Inc.
Publication Date: 10/1/1964
Pages: 23
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0448116
Photo Enhancement: Incomplete
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Specific Heat and Speed of Sound Data for Imperfect Nitrogen - I. T = 2000 to 15,000 Degrees K
Report Number: AEDC TDR 64-113
Author(s): Clark H. Lewis and Charles A. Neel
Corporate Author: ARO, Inc.
Publication Date: 6/1/1964
Pages: 149
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0601241
Photo Enhancement: Not Needed
Abstract Text:
Specific heat and speed of sound data were computed for imperfect nitrogen. The thermodynamic data included the effects of two-body intermolecular forces, and the results were obtained by numerical interpolation and differentiation of the recent data of Hilsenrath and Klein (AD-432 210). Results are given for the ranges T = 2000(100)15,000 K and log RHO = -6.8(0.2)2.2. Comparisons with previous perfect gas calculations showed small effects on the specific heat data at all pressures considered; however, at pressures near 1000 atm, the effects were larger on the speed of sound data. (For T = 100 to 2200 K see AD-601 205).
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Specific Heat and Speed of Sound Data for Imperfect Nitrogen - II. T = 100 to 2200 Degrees K
Report Number: AEDC TDR 64-114
Author(s): Clark H. Lewis and Charles A. Neel
Corporate Author: ARO, Inc.
Publication Date: 6/1/1964
Pages: 44
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0601205
Photo Enhancement: Not Needed
Abstract Text:
Specific heat and speed of sound data were computed for imperfect nitrogen in the range T = 100 to 2200 K (for T = 2000 to 15,000 K see AD-601 241). The thermodynamic data included the effects of intermolecular forces, and the results were obtained by numerical interpolation and differentiation of the thermodynamic data.
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Knife-Edge Controller for a Schlieren System
Report Number: AEDC TDR 64-126
Author(s): C. B. Wells
Corporate Author: ARO, Inc.
Publication Date: 6/1/1964
Pages: 17
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0441303
Photo Enhancement: Incomplete
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Summary Report on Aerodynamic Characteristics of Standard Models HB-1 and HB-2
Report Number: AEDC TDR 64-137
Author(s): J. Don Gray
Corporate Author: ARO, Inc.
Publication Date: 7/1/1964
Pages: 47
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0602769
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Abstract Text:
All available test data on the standard hypersonic ballistic correlation models, HB-1 and HB-2, were examined to establish reference characteristics for use in the correlation of experimental results among the various aerodynamic facilities. The data presented are comprised primarily of static stability and zero-lift forebody axial-force coefficient results at Mach numbers from about 1.5 to 20 for a Reynolds number range from 0.01 to 2700000 based on centerbody diameter. Selected pressure distribution, dynamic stability, and heat-transfer data are included. Comparisons of data from various test facilities show excellent correlation in spite of the appreciable Reynolds number dependence of test results for model HB-2 with natural boundary-layer transition.
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Aerodynamic Drag on Spiked Blunt Bodies in Low-Density Hypersonic Flow
Report Number: AEDC TDR 64-160
Author(s): William H. Sims and Jerry S. Hahn
Corporate Author: ARO, Inc.
Publication Date: 8/1/1964
Pages: 21
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0603567
Photo Enhancement: Incomplete
Abstract Text:
Aerodynamic drag on spiked blunt bodies was measured in hypersonic, low-density flow of nitrogen. Two models were tested: a spherically capped cone of 10-deg halfangle at 0 < alpha < 40 deg, and a right circular cylinder at alpha = 0. Reynolds numbers, based on total body lengths and free-stream conditions, varied from 200 to 1200. Mach number was constant at 10.1. Results were compared with modified Newtonian and free-molecule calculations. Effects of hypersonic rarefied flow are apparent, with drag coefficient increasing for large angles of attack for all spike lengths. A correlation procedure suggested in an earlier report for a large class of similar bodies at 0-deg angle of attack is shown to be effective in the case of spiked bodies too. It is apparent that the marked reduction of drag effected by use of spikes on blunt-nosed bodies at higher Reynolds numbers is greatly diminished when low Reynolds numbers exist. However, a moderate reduction is shown for small angles of attack at the Reynolds numbers of the present experiment.
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An Influence of the Orifice on Measured Pressures in Rarefied Flow
Report Number: AEDC TDR 64-175
Author(s): J. Leith Potter, Max Kinslow, and David E. Boylan
Corporate Author: ARO, Inc.
Publication Date: 9/1/1964
Pages: 28
Contract: AF 40(600)-1000
Project: 8950
Task: 895004
AD Number: AD0447734
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Analysis of Methods for Determining Outgassing Rates
Report Number: AEDC TDR 64-180
Author(s): J. I. Shipp and J. D. Trolinger
Corporate Author: ARO, Inc.
Publication Date: 12/1/1964
Pages: 21
Contract: AF 40(600)-1000
Project: 6950
Task: 695003
AD Number: AD0608660
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Abstract Text:
Methods of determining outgassing rates of materials under vacuum are discussed with emphasis on the accuracy and limitations of each. Pressure measurement techniques included are rate of evacuation, rate of rise, and a number of conductance methods. Assuming Langmuir's model for sticking probability, it is shown that these techniques can introduce large errors in determinations of desorption rates due to incorrect choice of pumping speed. Instrument calibration procedures and comparisons of results employing different techniques are also given.
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The Magnetohydrodynamic Arc Thruster
Report Number: AEDC TDR 64-182
Author(s): Peter A. Schoeck
Corporate Author: ARO, Inc.
Publication Date: 9/1/1964
Pages: 20
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0447481
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Interpolations of Imperfect Air Thermodynamic Data I. At Constant Entropy
Report Number: AEDC TDR 64-183
Author(s): C. A. Neel and Clark H. Lewis
Corporate Author: ARO, Inc.
Publication Date: 9/1/1964
Pages: 298
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0605471
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Abstract Text:
The recent thermodynamic air data of Hilsenrath and Klein (AEDC-TDR-63-161) and the previous low temperature data of Humphrey and Neel (AEDC-TN-61-103) have been interpolated at constant entropy over the ranges T = 100(100) 15,000K and S/R = 15.6(0.2)50, 50(1)133. Speed of sound data computed by Lewis and Neel (AEDC-TDR-64-36) are also included.
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Interpolations of Imperfect Air Thermodynamic Data II. At Constant Pressure
Report Number: AEDC TDR 64-184
Author(s): C. A. Neel and Clark H. Lewis
Corporate Author: ARO, Inc.
Publication Date: 9/1/1964
Pages: 217
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0446386
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Abstract Text:
The recent thermodynamic air data of Hilsenrath and Klein (AEDC-TDR-63-161) and the previous low temperature data of Humphrey and Neel (AEDC-TN- 61-103) have been interpolated at constant pressure over the ranges T = 100 (100) 15,000 K and log p = -6.4(0.1)4.0.
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Interpolations of Imperfect Nitrogen Thermodynamic Data I. At Constant Entropy
Report Number: AEDC TDR 64-212
Author(s): C. A. Neel and Clark H. Lewis
Corporate Author: ARO, Inc.
Publication Date: 10/1/1964
Pages: 378
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0449409
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Interpolations of Imperfect Nitrogen Thermodynamic Data II. At Constant Pressure
Report Number: AEDC TDR 64-213
Author(s): C. A. Neel and Clark H. Lewis
Corporate Author: ARO, Inc.
Publication Date: 10/1/1964
Pages: 229
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0449381
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