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Methods of Approximating Inviscid Jet Boundaries for Highly Underexpanded Supersonic Nozzles
Report Number: AEDC TDR 62-7
Author(s): J. R. Henson; J. E. Robertson
Corporate Author: Arnold Engineering Development Center
Laboratory: Arnold Engineering Development Center
Publication Date: 5/1/1962
Pages: 63
Contract: AF 40(600)-800
AD Number: AD0275641
Abstract Text:
Methods of approximating inviscid boundaries of jets exhausting from axisymmetric supersonic nozzles into a quiescent atmosphere and moving streams have been developed. Jet shapes from two typical afterbody configurations were calculated for various flight conditions. Good agreement with available theoretical and experimental data was obtained. A step-by-step calculational procedure is given in the Appendix.
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Development of a Gas Generator Using a Rocket-Type Combustor as the Heat Source
Report Number: AEDC TDR 62-15
Author(s): C. T. Carman
Corporate Author: Arnold Engineering Development Center
Laboratory: Arnold Engineering Development Center
Publication Date: 3/1/1962
Pages: 26
Contract: AF 40(600)-800
AD Number: AD0273488
Abstract Text:
An Investigation Was Conducted To Determine The Feasibility Of Producing Large Quantities Of Gas As The Driving Medium Of Steam Ejectors By Directly Mixing Water With The Exhaust Gas Stream Of A Rocket-Type Combustion Chamber. The Feasibility Of Producing Large Quantities Of Steam-Gas Mixture Was Demonstrated. Gas With Specific Humidities Below The Saturated Value Was More Suitable As An Ejector Driving Fluid Than Saturated Mixtures. He Evaporative Efficiency Of The Rocket Steam Generating Rig Was In The Range From 91 To 103 Percent.
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Performance Of A Two-Stage Launcher Using Hydrogen
Report Number: AEDC TDR 62-32
Author(s): W. B. Stephenson and R. E. Knapp
Corporate Author: ARO, Inc.
Laboratory: Arnold Engineering Development Center
Publication Date: 3/1/1962
Pages: 58
Contract: AF 40(600)-800
Project: 8950
Task: 89600
AD Number: AD0273528
Photo Enhancement: Not Needed
Abstract Text:
A procedure is outlined for computing the performance of two-stage, light-gas launchers using hydrogen as a propellant. A method in general dimensionless terms is developed by which the launch velocity for this type of launcher may be computed. The effects of piston weight and velocity, as well as preheating of the pump tube gas, are determined. Experimental results using both unheated and heated hydrogen are compared with theoretical calculations of velocity. Since the important physical variables -- piston mass, velocity, pump tube geometry, initial pump tube pressure, piston reversal, initial projectile movement, and heat losses -- are included, a design optimization has been made, and limits to the launch velocity were estimated.
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An Examination Of Epoxy Systems Useful In Packaging High G Radio Telemeters
Report Number: AEDC TDR 62-58
Author(s): R. P. Young
Corporate Author: ARO, Inc.
Laboratory: Arnold Engineering Development Center
Publication Date: 3/1/1962
Pages: 30
Contract: AF 40(600)-800
Project: 8952
Task: 895201
AD Number: AD0273681
Photo Enhancement: Complete
Abstract Text:
The electrical components used in high g (500,000 g) telemetry packages will survive gun launchings only if potted in suitable materials. The materials considered for this application were: polyesters, epoxies, silicones, phenolics, and urethanes. The epoxy materials appeared to fulfill most of the requirements for this application. This report described epoxy materials, their curing, methods of potting, and the tests performed to select an epoxy material for embedding telemetry packages launched from hypervelocity guns in aeroballistic ranges.
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A Device for Measuring Heat Transfer Rates in Arc-Discharge Hypervelocity Wind Tunnels
Report Number: AEDC TDR 62-64
Author(s): R. L. Ledford
Corporate Author: ARO, Inc.
Laboratory: Arnold Engineering Development Center
Publication Date: 5/1/1962
Pages: 37
Contract: AF 40(600)-800
Project: 8952
Task: 895201
AD Number: AD0275740
Photo Enhancement: Complete
Abstract Text:
Heat-transfer-rate is one of the fundamental aerodynamic parameters which must be measured in Hypervelocity wind tunnel testing. Transducers which can perform this measurement are not commercially available; therefore a device which can be employed for this purpose has been developed. This device can measure transient rates ranging from 1 to 1000 Btu/sq ft. sec for periods of 5 to 80 millisec; it does not require run-to-run calibration; and it is durable enough to withstand many tunnel runs without maintenance. Its performance has been proven through laboratory and tunnel tests and usage.
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The Effect Of Heat Release On The Flow Parameters In Shock-Induced Combustion
Report Number: AEDC TDR 62-78
Author(s): R. P. Rhodes, P. M. Rubins, and D. E. Chriss
Corporate Author: ARO, Inc.
Laboratory: Arnold Engineering Development Center
Publication Date: 5/1/1962
Pages: 76
Contract: AF 40(600)-800
Project: 6952
Task: 695201
AD Number: AD0275366
Photo Enhancement: Complete
Abstract Text:
Experimental investigations were conducted in a Mach 3 combustion tunnel to detemine heat release characteristics of a hydrogen-air mixture after it had passed through a normal shock. Inlet temperature varied from 1800 to 3000 degrees R. Heat relsease was indicated by three types of measurements: 1. Combustion and total temperature rise calculated from gas analysis. 2. Total pressure loss caused by heat addition. 3. Ultra-violet emmission at the OH emission frequencies, indicating an H2-O2 reaction. Combustion efficiency was found to increase with temperature and to be independent of fuel-air ratio. Fuel passing through an oblique shock was observed to emit a radiation similar to that observed from the normal shock combustion.
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Experience With An Overexpanded Nozzle In A Low-Density, Hypervelocity Wind Tunnel
Report Number: AEDC TDR 62-85
Author(s): J. Leith Potter and David E. Boylan
Corporate Author: ARO, Inc.
Laboratory: Arnold Engineering Development Center
Publication Date: 4/1/1962
Pages: 16
Contract: AF 40(600)-800
Project: 8950
Task: 895004
AD Number: AD0274383
Photo Enhancement: Not Needed
Abstract Text:
Detailed measurements of static and impact pressures in the nozzle of a low-density wind tunnel are presented. Purpose of the investigation was to determine the extent to which the nozzle of the Low-Density, Hypervelocity Tunnel may be used in an overexpanded mode of operation. Expansions to static pressure from one-fourth to one-fifth of the pressure outside the exit of the nozzl are shown to be feasible with the nozzle having a nominal Mach number of 10 and boundary-layer thickness approaching nozzle radius at the exit.
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A Pressure Data System For A 50-In. Continuous Mach 8 Wind Tunnel
Report Number: AEDC TDR 62-96
Author(s): F. C. Hightower, Jr.
Corporate Author: Arnold Engineering Development Center Arnold Air Force Station Tenn
Laboratory: Arnold Engineering Development Center
Publication Date: 5/1/1962
Pages: 30
Contract: AF 40(600)-800
Project: None Given
Task: None Given
AD Number: AD0275554
Photo Enhancement: Complete
Abstract Text:
This report is a description of a pressure data system designed and built for use with a 50-inch, continuous, Mach 8 wind tunnel. The system is basically a nine-channel system, with a capacity for 99 model pressure ports. Three ranges and seven reference pressure levels are employed to provide an extended pressure level coverage, while maintaining low-level sensitivity. Control circuits are employed to automatically select the proper range and refernce level for each pressure measurement, and to simplify calibration procedures. A description of the measuring and control systems components is included, along with a section on the operation of the control system. The report is concluded with an evaluation of the pressure data system, based on a two-year period of operation.
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Source Flow Effects In Conical Hypervelocity Nozzles
Report Number: AEDC TDR 62-116
Author(s): Jack D. Whitfield and Glenn D. Norfleet
Corporate Author: Arnold Engineering Development Center Arnold Air Force Station Tenn
Laboratory: Arnold Engineering Development Center
Publication Date: 6/1/1962
Pages: 20
Contract: AF 40(600)-800
Project: 8952
Task: 895202
AD Number: AD0276724
Photo Enhancement: Complete
Abstract Text:
Source flow effects in conical hypervelocity nozzles are studied by means of a simple Newtonian theory for slender conical bodies. Experiments were conducted to examine the validity of this simple theoretical approach and a semiempirical theory is developed to assess the magnitude of source flow effects. Significant source flow effects were found, and the need for contoured hypervelocity wind tunnel nozzles is shown.
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Compensation Of Dynamic Sting Effects In Hotshot Force Measurements
Report Number: AEDC TDR 62-122
Author(s): E. E. Edenfield and R. L. Ledford
Corporate Author: Arnold Engineering Development Center Arnold Air Force Station Tenn
Laboratory: Arnold Engineering Development Center
Publication Date: 6/1/1962
Pages: 34
Contract: AF 40(600)-800
Project: 8952
Task: 895201
AD Number: AD0277055
Photo Enhancement: Complete
Abstract Text:
A system which can substantially reduce the detrimental effects of sting vibrations of force measurements made in the von Karman Gas Dynamics Facility's Hotshot wind tunnels has been developed and proved effective. A description of this system and its theory of operation are presented along with the results of evaluation tests.
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Flow Characteristics Of A 40-Inch Wind Tunnel At Mach Numbers 1.5 To 6
Report Number: AEDC TDR 62-130
Author(s): Jack D. Coats
Corporate Author: Arnold Engineering Development Center Arnold Air Force Station Tenn
Laboratory: Arnold Engineering Development Center
Publication Date: 6/1/1962
Pages: 37
Contract: AF 40(600)-800
Project: None Given
Task: None Given
AD Number: AD0277289
Photo Enhancement: Complete
Abstract Text:
The flexible steel plate which forms the lower nozzle wall of the 40-in. Supersonic Tunnel of the von Karman Gas Dynamics Facility was damaged in October 1961. A brief description of the damage and repair of the plate is presented with flow characteristics obtained during a calibration program conducted after completion of the repairs. The calibration showed that the uniformity of the test-section flow characteristics was not adversely affected by the repair which included the use of a pattern of bolt heads protruding above the surface of the plate in the subsonic region of the nozzle.
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Inductive Power Supply For A Hotshot-Type Tunnel
Report Number: AEDC TDR 62-137
Author(s): A. H. Fillers, Jr.
Corporate Author: Arnold Engineering Development Center Arnold Air Force Station Tenn
Laboratory: Arnold Engineering Development Center
Publication Date: 7/1/1962
Pages: 53
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0278158
Photo Enhancement: Complete
Abstract Text:
This report covers the development and operation of a 5 times 10 to the 6th power joule, inductive-storage power supply for a hotshot-type wind tunnel. A discussion of the equipment and its auxiliaries is given.
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Radio Telemetry of Stagnation Pressure from a wind Tunnel Model Magnetically Supported in Supersonic Flow,
Report Number: AEDC TDR 62-141
Author(s): P. L. Clemens
Corporate Author: Arnold Engineering Development Center Arnold Air Force Station Tenn
Laboratory: Arnold Engineering Development Center
Publication Date: 7/1/1962
Pages: 25
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0278159
Photo Enhancement: Complete
Abstract Text:
During a set of aerodynamic tests in a Mach number 2.4 wind tunnel, it was proven feasible to telemeter stagnation pressure measurements from within a magnetically suspended, ferromagnetic model. State-of-the-art, f-m radio telemetry, developed for hypervelocity range use, was employed. Although data at the outset of each of three trials reflect errors of less than three percent, inordinate frequency vs temperature interactions introduced intolerable shifts in telemeter center frequency as testing progressed. Several methods may be used to reduce these interactions. Magnetogasdynamic effects arising from the use of the magnetic model suspension technique are discussed, and are shown to be negligible in most wind tunnel testing.
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Experimental Heat Transfer to Blunt Axisymmetric Bodies Near the Limit of Continuum Flow
Report Number: AEDC TDR 62-155
Author(s): J. Leith Potter and John T. Miller
Corporate Author: ARO, Inc.
Laboratory: Arnold Engineering Development Center
Publication Date: 8/1/1962
Pages: 20
Contract: AF 40(600)-1000
Project: 8953
Task: 895306
AD Number: AD0281911
Photo Enhancement: Not Needed
Abstract Text:
Measurements of average heat-transfer rates to blunt-nosed, axisymmetric, cold-walled bodies in a low-density, hypervelocity wind tunnel are given. Stream density was such that Reynolds and Knudsen numbers, based on nose radius and conditions immediately behind the bow shock, varied from 5 to 20 and 0.11 to 0.056, respectively. Thus, scaling on the basis of Knudsen number, these conditions may be said to simulate a body of one-foot nose radius at as much as 315,500-ft altitude. Heat-transfer rates are discussed in relation to the flow model successfully used in the past for studies of flows of high Reynolds number. In this context, it was found that measured heat-transfer rates to hemispheres below shock-layer Reynolds numbers of 20 exhibited a decreasing nondimensionalized rate relative to that estimated by methods appropriate to high Reynolds number conditions. This behavior is in accord with various applicable theories. Rates for the flat-faced bodies showed no tendency to decrease, and they were somewhat higher than predicted by theories for high Reynolds numbers.
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Fatigue Tests and Crack Detection on Some Types of Axial-Flow Compressor Rotor Blades
Report Number: AEDC TDR 62-168
Author(s): R. E. Thomas
Corporate Author: ARO, Inc.
Laboratory: Arnold Engineering Development Center
Publication Date: 10/1/1962
Pages: 34
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0287410
Photo Enhancement: Complete
Abstract Text:
Fatigue data were obtained from several types of compressor rotor blades that are in use in axial-flow compressors at the von Karman Gas Dynaics Facility. The data provided a general comparison of ''as manufactured'' endurance limits and were used as a veification control in evaluating a supplemenary method of detecting failed blades during sytematic maintenance inspections. By the presentation of stress versus cycles to failure curves, a comparison is ade between AISI number-8630 cast steel blades as originally furnished with the compressors, AISI number-8630 cast steel shot-peened blades, and AISI number-403 forged, heat-treated and machined blades. A method is presented which may be used to supplement the magnetic particle method for detecting cracked rotor blades. (Autho)AD-287 4109N3 +++Fatigue tests and crack detection on some types of axial flow compressor rotor blades. Data provided a general comparison of ''as manufactured' endurance limits and were used as a verifiction control in evaluating a suppplementary method of detecting failed blades.
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Tables of the Thermodynamic Properties of Nitrogen From 100 to 1500 Degrees K
Report Number: AEDC TDR 62-170
Author(s): Wanda J. Little and C. A. Neel
Corporate Author: ARO, Inc.
Laboratory: Arnold Engineering Development Center
Publication Date: 9/1/1962
Pages: 103
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0283441
Photo Enhancement: Not Needed
Abstract Text:
Tables of thermodynamic properties of nitrogen are presented for the range of temperatures from 100 to 1500 degrees Kelvin. In the first table, in which temperature and pressure are the independent variables, the range of pressures extends from one to 10 to the fourth atm. In the second table, with termperature and density as independent variables, the range of densities extends from 10 the the negative seventh to 630 amagats. In addition to pressure and density, the tabulated properties are the compressibility factor Z and the dimensionless functions E/RT, H/RT, and S/R. The source data and the tables are discussed.
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An Analysis of Nonequilibrium Inviscid Flow
Report Number: AEDC TDR 62-172
Author(s): W. E. Gibson and A. Sowydra
Corporate Author: Cornell Aeronautical, Inc.
Laboratory: Arnold Engineering Development Center
Publication Date: 8/1/1962
Pages: 73
Contract: AF 40(600)-928
Project: 8951
Task: 89103
AD Number: AD0282901
Photo Enhancement: Not Needed
Abstract Text:
An analytic solution is developed for blunt-body flows involving nonequilibrium chemistry. The chemical model describes a diatomic gas with a single dissociation recombination reaction. The progress of the reaction is determined behind the bow shock under conditions of vibrational equilibrium. The analysis seeks an improved understanding of the structure of the chemical relaxation zone along streamlines, in particular, its dependence on flow parameters. In high-altitude flight, three-body recombination becomes ineffective and dissociation or binary scaling can be applied. The range of validity of binary scaling is found and the implications for hypersonic testing are discussed. The analytic approach also applies for cases where recombination is important, including equilibrium flow. Numerical examples are given for spherical bodies and for a range of body sizes and flight altitudes.
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A Two-Color Pyrometer for the Measurement of Temperature and Contamination Level in a Spark-Heated Hypervelocity Wind Tunnel
Report Number: AEDC TDR 62-174
Author(s): Walter Vali and R. Stephen de Voto
Corporate Author: Stanford University
Laboratory: Arnold Engineering Development Center
Publication Date: 8/1/1962
Pages: 32
Contract: AF 40(600)-930
Project: 8952
Task: 895210
AD Number: AD0282928
Photo Enhancement: Complete
Abstract Text:
A description is given of exploratory measurements, by means of a two-color pyrometers, of the temperature and concentration of solid contaminants near the throat of a spark-heated hypervelocity wind tunnel. Because of its rapid response, the method is capable of providing a time-resolved history of the contamination during a run. Although some initial success can be reported, additional work remains to be done before the method can be made reliably quantitative and before the temperature of the flowing gas can be related to that of the contaminants.
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Calibration Tests of a Litton Conical Air Data Probe at Mach Numbers of 2 to 8
Report Number: AEDC TDR 62-186
Author(s): Scott R. Mallard
Corporate Author: ARO, Inc.
Publication Date: 10/1/1962
Pages: 22
Project: 0
Task: 0
AD Number: AD0292632
Photo Enhancement: Incomplete
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Addendum to an Investigation of the Equilibrium Pressure Along Unequally Heated Tubes
Report Number: AEDC TDR 62-188
Author(s): G. D. Arney, Jr., and A. B. Bailey
Corporate Author: ARO, Inc.
Laboratory: Arnold Engineering Development Center
Publication Date: 10/1/1962
Pages: 40
Contract: AF 40(600)-1000
Project: 8953
Task: 895306
AD Number: AD0286166
Photo Enhancement: Not Needed
Abstract Text:
This report presents results of an investigation of the error introduced in very low pressure measurements when small tubes with axial temperature gradients connect pressure tran ducer and the point where knowledge of the pressure is desired. The experiments reported in AEDC-TDR-62-26 were extended with air, argon, and helium to include higher Knudsen numbers and to include data taken with t e pressure transducer at the hot end of the tube. Although the form of the pressure-temperature relations ip was specified with good accuracy to a Knudsen number of 5.0, the degree of scatter for larger Knudsen numbers was s ch (!5%) tha it was not possible to fix accurately the free molecule limit. Also in the present analysis, what is considered to be a more accepted definition of mean free path is used, and the opportunity was taken to recalculate the earlier work using this definition.
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The Drag of Spheres in Rarefied Hypervelocity Flow
Report Number: AEDC TDR 62-205
Author(s): Max Kinslow and J. L. Potter
Corporate Author: ARO, Inc.
Laboratory: Arnold Engineering Development Center
Publication Date: 12/1/1962
Pages: 58
Contract: AF 40(600)-1000
Project: 8953
Task: 895306
AD Number: AD0290519
Photo Enhancement: Complete
Abstract Text:
Drag of spheres was measured under hypersonic, cold-wall, support-free conditions in a nonreacting (vibration frozen) flow. Data were obtained for a nominal free-stream Mach 11 and for Reynolds numbers from 1 to 10 based on conditions immediately downstream of the bow shock and sphere diameter. These data were supplemented by measurements at a nominal Mach 10 where a conventional balance was used, and Reynolds numbers downstream of the shock as high as 10,000 were investigated in the cold-wall condition. The experimental results were analyzed both from the point of view of continuum flow with second-order viscous effects, and from the standpoint of a noncontinuum concept, taking account of first collisions between reemitted and free-stream molecules. Data from other sources were used to enlarge the present study and, in particular, to support the evaluation of K2 which represents the influences of vorticity, curvature, thick boundary layer, slip, and temperature jump. K2 was found to be negative in sign. The form of the derived equation for Cd/Cd(free molecular), where Cd is the drag coefficient, Cd/Cd free molecular appears to fit the experimental data over a considerable range of Knudsen numbers if a free constant is used in the expression for mean free path.
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Further Experiments on Impact-Pressure Probes in a Low-Density, Hypervelocity Flow
Report Number: AEDC TDR 62-208
Author(s): A. B. Bailey
Corporate Author: ARO, Inc.
Laboratory: Arnold Engineering Development Center
Publication Date: 11/1/1962
Pages: 32
Contract: AF 40(600)-1000
Project: 8950
Task: 895004
AD Number: AD0290520
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Abstract Text:
An investigation of the behavior of flat-faced, impact-pressure probes with a range of orificeto-probe diameter ratios was made in heated A under conditions where free stream Mach. = 4 to 14, gas temperature = 2700 to 4300 K, and Reynolds number (based on outside probe diameter and conditions behind a normal shock)/in. = 30 to 430. At the lower Reynolds numbers the measured impact pressure was found to decrease with the pressure sensing orifice size. This result agrees with that found in heated N. As the Reynolds number increased this orifice effect became less significant, and at the higher Reynolds numbers no decrease in measured impact pressure was noted for the smallest orifice tested. This tends to confirm the assumption made in some experiments on impact-pressure probes in a low-density hypervelocity flow (AD-268 391) that this behavior is caused by a thermomolecular flow effect. Because this effect is a function solely of pressure at a particular temperature, the greater the pressure the smaller the effect. When Re2 times the square root of density in free stream over density in normal shock is less than 800 in A the measured impact pressure was less than the true impact pressure and decreased to a minimum value, approximately 93% of the true value. As the Reynolds number decreased still further, the viscous effects became dominant, and there was a sharp increase in the measured impact pressure.
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Microwave Measurement of Projectile Kinematics Within Launcher Barrels
Report Number: AEDC TDR 62-213
Author(s): R. E. Hendrix
Corporate Author: ARO, Inc.
Laboratory: Arnold Engineering Development Center
Publication Date: 11/1/1962
Pages: 37
Contract: AF 40(600)-1000
Project: 8950
Task: 895002
AD Number: AD0288923
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Abstract Text:
Microwave reflectometry has been applied successfully to the study of the kinematic behavior of projectiles within launcher barrels and pistons within compression (pump) tubes in the Hypervelocity Pilot Range of the von Karman Gas Dynamics Facility. Well-defined mathematical treatment enables the calculation of an accurate time history of projectile position inside its launcher barrel. Microwave excitation in extraneous modes has been attenuated, resulting in an increase in the accuracy of the reflectometer system.
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Measurements of Pressure and Speed of Flow in a Spark-Heated Hypersonic Wind Tunnel
Report Number: AEDC TDR 62-218
Author(s): Krishnamurty Karamcheti, Walter Vali, James B. Kyser, and Maurice L. Rasmussen
Corporate Author: Stanford University
Laboratory: Arnold Engineering Development Center
Publication Date: 11/1/1962
Pages: 57
Contract: AF 40(600)-930
Project: 8952
Task: 895210
AD Number: AD0288668
Photo Enhancement: Complete
Abstract Text:
The nature of the flow and state of the gas in the nozzle and test section of the Stanford spark-heated hypersonic wind tunnel was studied. Attention is given only to the pressure and speed-of-flow measurements. Results are presented for pitot pressures and wall static pressures. The speed of flow in the test section is derived from measurements made by spark-schlieren photographs of a disturbance created in the flow by means of a spark discharge. On the basis of these measurements, it is concluded that the actual stagnation enthalpy of the stream is likely to be different from the enthalpy calculated according to current practice. As a consequence, it is shown that serious errors may occur in the calculated values for the state of the flow, and in theoretical estimates of quantities such as stagnation-point heat-transfer rates.
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Evaluation of a Gas Bearing Pivot for a High Amplitude Dynamic Stability Balance
Report Number: AEDC TDR 62-221
Author(s): A. E. Hodapp, Jr.
Corporate Author: ARO, Inc.
Laboratory: Arnold Engineering Development Center
Publication Date: 12/1/1962
Pages: 18
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0290948
Photo Enhancement: Not Needed
Abstract Text:
The load capacity and damping level of a gas journal bearing are presented. Experimental data indicate that the bearing is capable of supporting radial loads in excess of 300 lb and that the damping parameter has some inverse relationship to frequency which is determined by the radial load. It is shown that the damped motion of the gas bearing can be approximated adequately with the viscous-damping equation.
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