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Inviscid and Viscous Hypersonic Nozzle Flow with Finite Rate Chemical Reactions
Report Number: AEDC TDR 63-18
Author(s): E. S. Levinsky and J. J. Brainerd
Corporate Author: General Dynamics/Astronautics
Laboratory: Arnold Engineering Development Center
Publication Date: 1/1/1963
Pages: 43
Contract: AF 40(600)-925
Project: 8952
Task: 895202
AD Number: AD0293448
Photo Enhancement: Not Needed
Abstract Text:
Procedures are developed for determining he inviscid core and boundary layer development in diverging nozzles with high enthalpy reservoir conditions in which the gas composition has been displaced fro equilibrium by chemical relaxation. A finite difference procedure, based on h method of characteristics, is used for the inviscid flow wit finite rate chemical reactions. Laminar boundary layer profiles, based on local similarity, are ob ained by integrating the coupled boundary layer and chemical reaction equations outward from the nozzle wall. Free stream boundary conditions on the c emical pecie concentrations and the th r odynamic variables are satisfied by i rati g o the unknow concentrations and derivatives at the wall. Numerical calculations are pr se ted for the AEDC, VKF low density tunnel and the Convair hypersonic shock tunnel. Effects of chemical reactions in the boundary layer are restricted o the region in which the core flow has not yet frozen and in which the boundary layer is thin. When the boundary layer is thick enough to influence the core expansion, ga p ase reactions are frozen.
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A Calorimetric Investigation of Some Problems Associated with a Low-Density Hypervelocity Wind Tunnel
Report Number: AEDC TDR 63-19
Author(s): G. D. Arney, Jr. and D. E. Boylan
Corporate Author: ARO, Inc.
Publication Date: 2/1/1963
Pages: 27
Contract: AF 40(600)-1000
Project: 8953
Task: 895306
AD Number: AD0295759
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Bibliography: The Magnetic Suspension of Wind Tunnel Models
Report Number: AEDC TDR 63-20
Author(s): P. L. Clemens and A. H. Cortner
Corporate Author: ARO, Inc.
Publication Date: 2/1/1963
Pages: 28
Contract: AF 40(600)-1000
Project: 8952
Task: 895201
AD Number: AD0296400
Photo Enhancement: Not Needed
Abstract Text:
This is a selective bibliography of the literature on the magnetic suspension of wind tunnel models including a chronological arrangement of titles and abstracts under four main headings: magnetic suspension for aerodynamic testing; non-aerodynamic applications of magnetic suspension; magnetic circuits and their electronic controls; and telemetry from magnetically supported aerodynamic models. An introduction presents a resume of the state-of-the-art of magnetic model suspension technology.
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The Shock Shape and Shock Detachment Distance for Spheres and Flat-Faced Bodies in Low-Density, Hypervelocity, Argon Flow
Report Number: AEDC TDR 63-21
Author(s): A. B. Bailey and W. H. Sims
Corporate Author: ARO, Inc.
Publication Date: 2/1/1963
Pages: 57
Contract: AF 40(600)-1000
Project: 8953
Task: 895306
AD Number: AD0297197
Photo Enhancement: Incomplete
Abstract Text:
An experimental investigation was made to determine the pressure distribution, shock shape, and shock detachment distance for spheres and the latter two characteristics for flatfaced bodies in a heated argon flow. The modified Newtonian approximation for the pressure distribution, which is strictly an empirical relationship, gives good results when applied to the first 60 degrees of a hemisphere under conditions where the body boundary layer and the shock layer merge. The natural flow visualization produced as a result of the high total temperature and consequent excitation of the argon enabled this study to be made. Photographs taken of the shocks generated by a series of spheres and flat-faced bodies were analyzed with a photo-densitometer to determine the shock shape and shock detachment distance. The blast analogy predicts a difference in the shape of shocks in argon and air at high Mach numbers and Reynolds numbers. An empirical relationship proposed by love was used to calculate the shock shape in air for Mach numbers corresponding to those of the present investigation.
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Low-Density Hypervelocity Wind Tunnel Diffuser Performance
Report Number: AEDC TDR 63-30
Author(s): M. W. Milligan; J. F. Bailey
Corporate Author: University of Tennessee
Publication Date: 1/1/1963
Pages: 48
Contract: AF 40(600)-922
Project: 8952
Task: None Given
AD Number: AD0295507
Photo Enhancement: Not Needed
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Vibrational Nonequilibrium with Nitrogen in Low-Density Flow
Report Number: AEDC TDR 63-31
Author(s): Alexander D. Lewis and George D. Arney, Jr.
Corporate Author: ARO, Inc.
Publication Date: 3/1/1963
Pages: 24
Contract: AF 40(600)-1000
Project: 8953
Task: 895306
AD Number: AD0298320
Photo Enhancement: Not Needed
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Calibration of the 100-Inch Hypervelocity Tunnel (F)
Report Number: AEDC TDR 63-46
Author(s): Henry W. Ball
Corporate Author: ARO, Inc.
Publication Date: 3/1/1963
Pages: 28
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0298279
Photo Enhancement: Incomplete
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Some Aspects of Energy Transfer in the Electrode and Settling Sections of an Arc-Heated Wind Tunnel
Report Number: AEDC TDR 63-72
Author(s): William H. Carden
Corporate Author: ARO, Inc.
Publication Date: 4/1/1963
Pages: 28
Contract: AF 40(600)-1000
Project: 8950
Task: 895004
AD Number: AD0401921
Photo Enhancement: Incomplete
Abstract Text:
A calorimetric investigation of certain energy transfer processes in the settling region of an arc-heated wind tunnel has been made. The effects of anode length and diameter on heat-transfer rates in he stilling chamber have been studied for a range of flow conditions. A radiation-cooled heat shield for use in the stilling chamber has been proposed and evaluated. A 20-percent reduction in the stilling chamber heat loss and a five-percent gain in overall efficiency are indicated with the installation of a suitable heat shield.
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Problems Underlying the Numerical Integration of the Chemical and Vibrational Rate Equations in a Near-Equilibrium Flow
Report Number: AEDC TDR 63-82
Author(s): George Emanuel
Corporate Author: Stanford University
Publication Date: 3/1/1963
Pages: 68
Contract: AF 40(600)-930
Project: 8952
Task: 895210
AD Number: AD0400745
Photo Enhancement: Not Needed
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An Analysis of Initial Static Pressure Probe Measurements in a Low-Density Hypervelocity Wind Tunnel
Report Number: AEDC TDR 63-94
Author(s): David E. Boylan
Corporate Author: ARO, Inc.
Publication Date: 4/1/1963
Pages: 16
Contract: AF 40(600)-1000
Project: 8950
Task: 895004
AD Number: AD0402935
Photo Enhancement: Not Needed
Abstract Text:
An initial experimental program was previously conducted to study the problems in using static pressure probes for flow calibration purposes in low-density, hypervelocity wind tunnels with continuous flow. This data is reviewed in the light of more recent data on thermal transpira tion. Results indicate that such probes may be used for what might be termed secondary calibra tions, but care is required in interpreting the results. The present experiment yielded data which are compared to static pressures calculated from impact-pressure probe calibrations.
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A Study of Laminar Heat Transfer to Spherically Blunted Cones and Hemisphere-Cylinders at Hypersonic Conitions
Report Number: AEDC TDR 63-102
Author(s): B. J. Griffith and Clark H. Lewis
Corporate Author: ARO, Inc.
Publication Date: 6/1/1963
Pages: 27
Contract: AF 40(600)-1000
Project: 8951
Task: 895103
AD Number: AD0408568
Photo Enhancement: Incomplete
Abstract Text:
Heat-transfer distribution data obtained in the arc-driven tunnels (hotshot type) of the von Karman Gas Dynamics Facility, AEDC, are pre sented. Data were taken on a 9-deg half-angle spherically bluqu 17 and 20 and Reynolds numbers per foot in the free-stream between 100,000 and 800,000. The test data are compared with theory and available shock tube and shock tunnel results. Good agreement between Lees' theory and measured heat-transfer rates demonstrates the capability of the VKF hotshot tunnels to obtain heat-transfer distribution data. The data indicate a strong dependence of the heat-transfer distribution on pressure dis tribution, Mach number, and cone half-angle. The heat-transfer data are correlated over a wide range of Mach numbers and cone angles. Correla tion curves and formulas are presented for the pressure and heat-transfer distribution to spherically blunted cones at hypersonic con ditions.
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Investigation of Boundary-Layer Transition on Swept Wings at Mach Numbers 2.5 to 5
Report Number: AEDC TDR 63-109
Author(s): S. R. Pate; R. E. Brillhart
Corporate Author: ARO, Inc.
Publication Date: 7/1/1963
Pages: 41
Contract: AF 40(600)-1000
Project: 1366
Task: 136612
AD Number: AD0410130
Photo Enhancement: Incomplete
Abstract Text:
Tests were conducted in the 12-in. Supersonic Tunnel of the von Karman Gas Dynamics Facility to determine boundary-layer transition locations on swept wings having a circular arc profile and modified arc profile. Test Mach numbers were from 2.5 to 5 over a Reynolds-number-per-inch range from 0.14 to 1. 08 million at sweep angles of 24, 36, and 50 deg for angles of attack of 0 and approximately -4 deg. Boundary-layer transition Reynolds numbers determined by a pitot probe, and results obtained visually with a sub limable solid are presented. The major factors influencing boundary-layer transition were wing sweep and model leading edge geometry. Increasing wing sweep and leading edge bluntness above a sweep angle of approximately 20 deg decreased the transition Reynolds number at all test Mach numbers.
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Nozzle Control System for a 40 by 40 Inch Supersonic Wind Tunnel
Report Number: AEDC TDR 63-129
Author(s): C. B. Wells
Corporate Author: ARO, Inc.
Publication Date: 7/1/1963
Pages: 36
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0409798
Photo Enhancement: Not Needed
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Variable Reluctance Pressure Transducer Development
Report Number: AEDC TDR 63-135
Author(s): W. E. Smotherman; W. V. Maddox
Corporate Author: ARO, Inc.
Publication Date: 7/1/1963
Pages: 37
Contract: AF 40(600)-1000
Project: 8952
Task: 895201
AD Number: AD0410171
Photo Enhancement: Incomplete
Abstract Text:
Pressure is one of the fundamental aerodynamic parameters which must be measured in hyperveloc ity wind tunnel testing. Pressure transducers whose time response and pressure ranges are suit able for test section measurements in the hyper velocity tunnels of the von Karman Gas Dynamics Facility (VKF) have been developed by the Instru mentation Branch of that facility. A description of these transducers, their theory of operation, and their performance characteristics are pre sented.
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Force Tests of Standard Hypervelocity Ballistic Models HB-1 and HB-2 at Mach 1.5 to 10
Report Number: AEDC TDR 63-137
Author(s): J. Don Gray; E. Earl Lindsay
Corporate Author: ARO, Inc.
Publication Date: 8/1/1963
Pages: 32
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0412651
Photo Enhancement: Incomplete
Abstract Text:
The aerodynamic characteristics of two standard, hypervelocity, ballistic-type models, designated HB-1 and HB-2 were investigated in the supersonic and hypersonic regimes. The tests were conducted at nominal Mach numbers of 1.5, 2, 3, 4, 5, 8, and 10 at Reynolds numbers from 0.07 to 2.55 x 10 to the 6th power, based on body diameter, and through an angle-of-attack range from -2 to 15 deg. The effects of Mach number, Reynolds number, and model attitude on the static stabil ity and axial-force characteristics of the two configurations were investigated. The zero-lift, forebody, axial-force coefficient, CA, for both configurations was found to be sensitive to Reynolds number variations; whereas the initial normal-force curve slope, CN alpha, and center of-pressure, xcp/l, for only the flared-tail model (HB-2) were dependent upon the Reynolds number.
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Empirical Equations for the Thermodynamic Properties of Air and Nitrogen to 15,000 K
Report Number: AEDC TDR 63-138
Author(s): Clark H. Lewis
Corporate Author: ARO, Inc.
Publication Date: 7/1/1963
Pages: 43
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0411624
Photo Enhancement: Not Needed
Abstract Text:
Empirical equations were obtained for equilibrium dissociating and ionizing air and nitrogen for temperatures up to 15,000 K and in the entropy range 1.42 < log (S/R) < 2.06. The corresponding density range is approximately 10-6 to 102 amagats. The density (p,S), enthalpy H(p,S), compressibility factor Z(p,S), and speed of sound a(p,S) are presented in equation form and as an IBM Fortran subroutine program. The errors in each empirical surface are indicated.
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Charts of Sphere Stagnation Heat-Transfer Rate in Air and Nitrogen at High Temperatures
Report Number: AEDC TDR 63-139
Author(s): Clark H. Lewis
Corporate Author: ARO, Inc.
Publication Date: 7/1/1963
Pages: 17
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0409870
Photo Enhancement: Not Needed
Abstract Text:
Fay and Riddell's theory for laminar heat trans fer at the stagnation point is applied to the sphere in equilibrium air and nitrogen. Charts are presented of the heat-transfer rate as a function of stagnation temperature and pressure or free-stream velocity and stagnation pressure in the pressure range between 0.1 and 10 A. and in the temperature range from 2000 to 15,000 K. The effects of Lewis number are considered. Com parisons between Fay and Riddell's theory, the recent theory of Fay and Kemp, and Shock-tube experiments are presented.
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Partition Functions and Thermodynamic Properties of Argon Plasma
Report Number: AEDC TDR 63-146
Author(s): K. S. Drellishak; C. F. Knopp; Ali Bulent Cambel
Corporate Author: Northwestern University
Publication Date: 8/1/1963
Pages: 238
Contract: AF 40(600)-748
Project: 8951
Task: 895104
AD Number: AD0414708
Photo Enhancement: Not Needed
Abstract Text:
Using tabulated data for observed atomic energy levels plus estimated energies for levels which are predicted but not observed, the internal partition functions for the argon atom and the first four argon ions were calculated on an IBM 709 computer. The partition functions were terminated by application of the Debye cutoff criterion and a corresponding lowering of the ionization potential was included. Assuming a mixture of six perfect gases (electrons, argon atoms, and argon ions) the equilibrium composition, internal partition functions and thermodynamic properties were calculated and tabulated for five pressures (0.1, 0.5, 1.0, 2.0, and 5.0 atmospheres) at 100 K increments for a range of temperatures from 5000 to 35000 K. The tables and figures include internal partition functions, composition, density, entropy, internal energy, enthalpy, Gibbs and Helmholtz potentials, specific heats at constant pressure and volume, the effective gamma and equilibrium sound speed.
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Basic Mechanisms of Noncondensable Gas Cryotrapping
Report Number: AEDC TDR 63-147
Author(s):
Corporate Author: General Technology Corporation
Publication Date: 7/1/1963
Pages: 58
Contract: AF 40(600)-941
Project: 6950
Task: 695001
AD Number: AD0410735
Photo Enhancement: Incomplete
Notes: Cover tile has "Cryotrapping". So do the index cards. Title page title has "Cryopumping". So does STINET.
Abstract Text:
Systematic measurements are reported on the rate at which argon and nitrogen are trapped by water as it condenses under vacuum onto a 77 K surface. For condensation rates between 10 to the 15th power and 10 to the 18th power molecules per sq. cm -sec. and noncondensable partial pressures between 0.000001 and 0.1 torr, trapping rates are proportional to condensation rate and a concen tration of adsorbed gas. The latter are described by Langmuir isotherms with characteristic pres sures for saturation of 0.0025 torr and 0.0035 torr for nitrogen and argon respectively. Inde pendent adsorption measurements show that quantity of gas adsorbed is proportional to mass of con densate (approximately 600 sq. meters per gram) and depends on pressure identically with the trap ping. Apparent trapping due to adsorption on surface area generated during condensation is only about 7% of actual trapping. All the results are consistent with a mixed phase for the con densate of which approximately 10% is the 12A gas hydrate.
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Tables of Thermodynamic Properties of Air in Chemical Equilibrium Including Second Virial Corrections from 1500 K to 15,000 K
Report Number: AEDC TDR 63-161
Author(s): Joseph Hilsenrath; Max Klein
Corporate Author: National Bureau of Standards
Publication Date: 8/1/1963
Pages: 203
Contract: DO 40(600)59-24
Project: 8950
Task: 895003
AD Number: AD0612301
Photo Enhancement: Not Needed
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Pressure Distribution and Flow Visualization Tests of a 1.5 Elliptic Cone at Mach 10
Report Number: AEDC TDR 63-163
Author(s): R. L. Palko; A. D. Ray
Corporate Author: ARO, Inc.
Publication Date: 8/1/1963
Pages: 55
Contract: AF 40(600)-1000
Project: 1366
Task: 136607
AD Number: AD0414567
Photo Enhancement: Incomplete
Abstract Text:
Results are presented for tests conducted on a 1.5 elliptic cone to determine the pressure distribution, flow streamlines, and shock wave shape at high angles of attack. The tests were performed at a Mach number of 10 and a freestream unit Reynolds number of 1.6 x 10 to the 6th power per foot. The angle-of-attack range was from 0 to 60 deg. The model was oriented both with the major and the minor axis of the ellipse located in the pitch plane.
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Pressures in the Stagnation Regions of Blunt Bodies in the Viscous-Layer to Merged-Layer Regimes of Rarefied Flow
Report Number: AEDC TDR 63-168
Author(s): J. Leith Potter; Allan B. Bailey
Corporate Author: ARO, Inc.
Publication Date: 9/1/1963
Pages: 46
Contract: AF 40(600)-1000
Project: 8953
Task: 895306
AD Number: AD0416004
Photo Enhancement: Not Needed
Abstract Text:
Experimental data on pressures in the stagnation regions of hemispherical and flat noses on axi symmetric bodies in rarefied, hypersonic flow are presented. Diatomic and monatomic gases were used in the study, thereby illustrating the effect of molecular structure on the impact pres sure. The experiments were conducted with the models in both cold-wall and insulated-wall con ditions. It is concluded that impact pressures may be smaller than the corresponding inviscid values, although this reduction may amount to only a few percent. Small influences of wall heat transfer and molecular structure on impact pressure at a given Reynolds number are demon strated. Pressure distribution on highly cooled, flat and hemispherical noses are predicted with generally acceptable accuracy by theories for inviscid flows. Flow conditions for these ex periments were such that the Knudsen number of a full-scale nose having a radius of one foot and moving with hypersonic speed at altitudes of roughly 300,000 ft was duplicated. Thus, this report concerns the viscous-layer to merged-layer regimes of flow at altitudes above Earth where thermochemical reactions in the shock layers of blunt bodies are believed to be e 0ially frozen.
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Hypersonic Force, Pressure, and Heat Transfer Investigations of Sharp and Blunt Slender Cones
Report Number: AEDC TDR 63-177
Author(s): David B. Wilkinson; Shelby A. Harrington
Corporate Author: Cornell Aeronautical Laboratory, Inc.
Publication Date: 8/1/1963
Pages: 143
Contract: AF 40(600)-928
Project: 8951
Task: 895103
AD Number: AD0414616
Photo Enhancement: Incomplete
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A Technique for Measuring a Local Gas Density Using Scattered Gamma Radiation
Report Number: AEDC TDR 63-187
Author(s): J.E. Shepard; J.B. Dicks
Corporate Author: ARO, Inc.
Publication Date: 11/1/1963
Pages: 33
Contract: AF 40(600)-1000
Project: 8951
Task: None Given
AD Number: AD0423150
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Abstract Text:
A method for direct density measurement of a gas without the use of material probes is proposed and the experimental investigation summarized. The operation of the gas density measuring instrument is based upon the interaction between a gamma-ray beam and the electrons in the gas as described by the Compton scattering principle. Experimental results indicate the practicability of this instrument for use in low density, high temperature wind tunnels and other high temperature gas flows such as rocket exhausts.
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Mollier Diagram for Air
Report Number: AEDC TDR 63-190
Author(s): Wanda J. Little
Corporate Author: ARO, Inc.
Publication Date: 9/1/1963
Pages: 36
Contract: AF 40(600)-1000
Project: 8951
Task: 89603
AD Number: AD0418575
Photo Enhancement: Not Needed
Abstract Text:
A Mollier diagram for air, including the effects of dissociation and ionization, as well as of intermolecular potentials to the second virial correction, is presented. The range of tempera tures extends from the saturation line to 15,000 K and the range odensities, from 10 to the -7th power to approximately 200 amagats.
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Boundary-Layer Characteristics at Mac Numbers 2 through 5 in the Test Section of the 12-Inch Supersonic Tunnel
Report Number: AEDC TDR 63-192
Author(s): D. R. Bell
Corporate Author: ARO, Inc.
Publication Date: 9/1/1963
Pages: 16
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0418711
Photo Enhancement: Incomplete
Abstract Text:
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.
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Flow Characteristics of A 12-In. Intermittent Supersonic Tunnel
Report Number: AEDC TDR 63-203
Author(s): A. Anderson
Corporate Author: ARO, Inc.
Publication Date: 9/1/1963
Pages: 37
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0418578
Photo Enhancement: Incomplete
Abstract Text:
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 pre sented 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 con tours 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 angu larity 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.
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Development of a Computer Program for the Analysis of One-Dimensional Magnetohydrodynamic Flow Problems
Report Number: AEDC TDR 63-215
Author(s): D. R. Wilson; C.E. Clouse; W.J. Schaetzle
Corporate Author: ARO, Inc.
Publication Date: 1/1/1964
Pages: 54
Contract: AF 40(600)-1000
Project: 7778
Task: 777805
AD Number: AD0426358
Photo Enhancement: Not Needed
Abstract Text:
A general method was developed for the analysis of one-dimensional magnetohydrodynamic channel flow problems. The basic differential equations for one-dimensional flow (influence coefficient equations) are discussed, and it is shown how the magnetohydrodynamic body force and joule heating are included. Methods are also presented for including the effects of area change, external heat exchange and wall friction; approximate methods for including real gas effects are mentioned. The resulting set of equations was programmed for solution on the IBM 7070 digital computer. A description of the computer program is given, and the complete Fortran listing of the main program and subroutines is presented. The accuracy of the program was checked by duplicating existing analytic or numerical solutions. Several typical calculations are presented as examples of the range of application of the method.
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Transformation of Axes Systems by Matrix Methods and Application to Wind Tunnel Data Reduction
Report Number: AEDC TDR 63-224
Author(s): L.L. Trimmer; E.L. Clark
Corporate Author: ARO, Inc.
Publication Date: 10/1/1963
Pages: 15
Contract: AF 40(600)-1000
Project: None Given
Task: None Given
AD Number: AD0422287
Photo Enhancement: Not Needed
Abstract Text:
A method is described which simplifies the derivation of many wind tunnel data reduction equations. Standard matrix techniques are used for the solution of the simultaneous equations encountered in the transformation of vector components from one axes system to another. Two typical applications are presented: the determination of aero dynamic angles and the transfer of aerodynamic loads from body to wind axes.
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Gasdynamic Diagnosis of High-Speed Flows Expanded From Plasma States
Report Number: AEDC TDR 63-241
Author(s): J. Leith Potter; George D. Arney, Jr.; Max Kinslow; William H. Carden
Corporate Author: ARO, Inc.
Publication Date: 11/1/1963
Pages: 43
Contract: AF 40(600)-1000
Project: 8950
Task: 895004
AD Number: AD0423983
Photo Enhancement: Incomplete
Abstract Text:
A number of methods of determining quantities are described which define the flow in lowdensity, hypersonic wind tunnels which use plasma generators to heat the working fluid. Although the fluid was heated to a plasma state initially, with a typical bulk temperature of 12,000 R, the measurements reported were for the purpose of calibrating the flow in the aerodynamic nozzle of a wind tunnel where it is descriable that the fluid be recombined before or during the expansion to high speeds. All of the methods considered may be classed as gasdynamic or aerodynamic as opposed to, say, spectroscopic methods. Measurements of total enthalpy, total and static pressure, and local mass flux are discussed, with descriptions of the equipment and typical results included. The emphasis is placed on procedures not requiring assumptions for the data reduction which cannot be checked. An appendix containing an account of the effect on nozzle flow which was caused by one method of swirling gas injection into the plasma generator electrode section is also included.
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