AD-A093 929 ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS N F/G 14/2

LASER SCATTERING APPLICATIONS DEVELOPMENT TEST IN AEDC TUNNEL B--ETC(U)MAR 50 W T STRIKE,

L L PRICE

UNCLASSIFIEO AEOC-TSR-80-V16 NL

ENOEMONEEI' llIllllllE EMMllllllllll

AEDC-TSR-80-V 16 LEVw,

LASER SCATTERING APPLICATIONS DEVELOPMENT TEST INAEDC TUNNEL B AT -MACH NUMBER 8

W. T. Strike and L. L. Price

_AR-, Inc.

March 1980

- Final Report for Period January 16, 1980 to February 12, 1980

C I

Approved for public relesue; distribution unlimnited. c

ARNOLD ENGINEERING DEVELOPMENT CENTERARNOLD AIR FORCE STATION, TENNESSEE

AIR FORCE SYSTEMS COMMANDUNITED STATES AIR FORCE

81 1 19 07. . . . .--- _ .I I IW " ' - I I

NOTICES

When U. S. Government drawinp, specifications, or other data are used for any purpose other "Tthan a definitely related Government procurement operation, the Government thereby incurs noresponsibility nor any obligation whatsoever, and the fact that the Government may haveformulated, furnished, or in any way supplied the said drawings, specifications, or other data, isnot to be regarded by implication or otherwise, or in any manner licensing the holder or anyother person or corporation, or conveying any Nights or permission to manufacture, use, or sellany patented invention that may in any way be related thereto.

References to named commeical products in this report are not to be considered in any sense Ias an indorsement of the product by the United States Air Force or the Government.

I'

APPROVAL STATEMENT

This report has been reviewed and approved.

LARRY H. DAVIS, 2d Lt, USAFTest Director, VKF DivisionDirectorate of Test Operations

Approved for publicatiot:

FOR THE COMMANDER

JOHN C. HARTNEY, Colonel USAFDirector of Test OperationsDeputy for Operations "

UNCLASSIFIEDL" REPORT DOCUMENTATION PAGE RED CNSTRCTIOSMJ , cs BEECOMPLETING FORM

AECl R -Vi-. GOVT ACCESSION NO. 3 IPIENVS CATALOG NUMBER

N -" "-; "Zrr"- R IP ,P RIOD COVErRED

-. _;,ASER$CATTERING .. PLICATIONS.EVELOPMENT TEST F ,Jan. 16-Feb.

IN fN§OTUNNELBXTMC UBf rzIyo- - . - _ PERFORMING ORG. REPORT NUMBER

AUTIOR(s) S CONTRACT OR GRANT NUMBER(s)

W. T. Strike L ARO, Inc., aI v erd up Corporation Cbmpany

9. PERFORMING ORGANIZATION NAME AND ADDRESS 10. PROGRAM ELEMENT. PROJECT, TASK

II.~~~AE COTOLN OWORC NAIE ANDMADRES

Arnold Engineering Development Center/DO ARAAir Force Systems Command Program Element 65807FArnold Air Force Station, TN 37389

II. CONTROLLING OFFICE NAME AND ADDRESS •

Arnold Engineeering Development Center/DOT raAir Force Systems Command -13. NUMBROF PAGESArnold Air Force Station, TN 373897

14. MONITORING AGENCY NAME & ADDRESS(/ different from Controlling Office) 15. SECURITY CLASS. (of this report)

. . UNCLASSIFIED

Sa. DECLASSIFICATION'DOWNGRAOING

SCHEDULE N/A16. DISTRIBUTION STATEMENT (of thsl Report)

Approved for public release; distribution unlimited.

17. DISTRIBUTION STATEMENT (of the abstract mitered In Block 20. If different f6om Report)

IS. SUPPLEMENTARY NOTES

Available in Defense Technical Information Center (DTIC).

19. KEY WORDS (Continue on rovers* side It necessary end Identity by block number)

laser scattering measuresurface press dataFabry-Perot interferometerwind tunnel test

Za.%,B.TRACT (Continu, on reve,..e id It necessary and identi y by block number)Free stream and local flow field measurements on a blunt (0.375-in. radius)

ndse 5-deg cone were made in Tunnel B at Mach number 8. The nonintrusive* flow field measurements were made using various laser scattering optical systems

to determine the free stream and local flow field particulate concentration andsize distribution, the nitrogen molecule number density, and the local streamvelocity using a Fabry-Perot interferometer system. The 5-deg cone pressuredistributions were used to confirm the test section Mach number and to producea known local flow field which could be utsed to demonstrate potentially _> Cow

DD I AN7, 1473 ED|TIOw OF I NOV SS IS OBSOLETEkaeUNCLASSIFIED

UNCLASSIFIED

20. ABSTRACT

useful laser scattering measuring techniques.

J1,1

AV$A'

11A.1 AV$ T..

UNCLASSIFIED

.I

CONTENTS

Page

NOMENCLATURE ....................... 21.0 INTRODUCTION ........... ....................... 42.0 APPARATUS

2.1 Test Facility .......... .................... 52.2 Test Article .......... ..................... 52.3 Laser-Scattering System ............... 6...........2.4 Standard Test Instrumentation. .. ............ 7

3.0 TEST DESCRIPTION3.1 Test Conditions and Procedures

3.1.1 General ......... ................... 73.1.2 Test Procedure ..... ................... 83.1.3 Data Acquisition .... ................... 8

3.2 Data Reduction ......... ................... 83.3 Measurement Uncertainty ....... ............... 9

4.0 DATA PACKAGE PRESENTATION ........ ................ 9REFERENCES ......... ........................ .... 10

APPENDIXES

I. ILLUSTRATIONS

Figure

1. Tunnel B ......... ........................ ... 122. VKF Standard Cone-Pressure Model ... ............. .... 133. Tunnel B Installation for Laser Scattering Test ..... . 144. Laser-Photomultiplier Detector Installation with Model

Injected ........................... 155. Dual Laser Installation, Nonoperating Side of Tunnel B . 166. Laser-Optics Installation on the Operating Side of Tunnel B 197. Laser-Optics System as Viewed from within the Tunnel,

Operating Side ........... ...................... 238. Laser-Optics System as Viewed from within the Tunnel,

Nonoperating Side ........ .................... ... 249. Optical Recording System on Top of Tunnel B ....... ... 25

10. 5-Deg Blunt Cone (Calibration Body) Pressure Distributions 27

II. TABLES

1. Estimated Uncertainties ..... .............. .... 372. VKF Tunnel B Test Log ...... .................. ... 30

III. DATA PACKAGE FORMATS

1. Typical Pressure Distribution Tabulations . ........ . 442. Typical Laser-Optics Tabulations ... ............. .... 46

I .

0i

NOMENCLATURE

ALPHA, a Sector Angle (prebend angle was 12.0 deg), deg

C.R. Center of Rotation, in.

DATA TYPE Defines the type of measurement and thesampling procedure

1. Laser data consisting of 300 samples at0.03 sec between points

2. Pressure data consisting of 40 samples atusually 1.0 sec between points

K Weighting factor for the time constant in thepressure prediction routine, in. 2/(lbf-sec)

LILM Laser internal light meter output, mv

LRPM Laser receiver power meter output, my

M Free stream Mach number

OMEGA, PHI Angular circumferential station, deg

P Free stream static pressure, psia

PDn Output of photomultiplier detector number "n", mv

PNN,PPN Measured model nose local stagnation surface

pressure, psia

PREF Reference pressure, uHg

PRMS Root-mean-square of the curve fitted time historyof the pressure with respect to the measuredpressure-time history, psi

PT Stilling chamber pressure, psia

PT2,PTS Computed stagnation pressure downstream of anormal shock, psia

PW Model surface pressure, psia

PWI Initial pressure measured in the time historyof the stabilizing model surface pressure, psia

PWF Final pressure measured in the time history ofthe stabilizing model surface pressure, psia

RATIO Ratio of LRPM/LILM in percent

RE Reynolds number per ft

2

RHO Free stream static density, lbm/ft3

RN Blunt nose cone radius (0.375 in.), in.

S Cone surface length relative to the bluntnose stagnation point, in.

TOUT Nitrogen concentration output

TT Stilling chamber total temperature, OR

U Free stream velocity, ft/sec

X Model station measured from theoretical apex ofthe blunt 5 deg cone, in.

I

IL

.3_. .. . .-,_ j . _ .. .. . -T, ... . ."i '

1.0 INTRODUCTION

The work reported herin was conducted by the Arnold EngineeringDevelopment Center (AEDC), Air Force Systems Command (AFSC), under

Program Element 65807F, for the Director of Technology (DOT) at AEDC.

The DOT project manager was Capt. Ken Leners and the ARO, Inc. projectmonitor was Mr. L. L. Price. The results were obtained by ARO, Inc.,AEDC Group (a Sverdrup Corporation Company), operating contractor for

the AEDC, AFSC, Arnold Air Force Station, Tennessee. The test was con-ducted in the von Karman Gas Dynamics Facility (VKF), Hypersonic WindTunnel .(B) during the period January 16, 1980 to February 12, 1980under ARO Project No. V41B-45.

This test program is to support the research effort entitled "Laser

Scattering Applications." The research effort is concerned with thedevelopment of laser scattdring applications to be used in satisfyingfuture AEDC test requirements. One task in this research effort is the

development and application of advanced laser. scattering optical systemsto measure flow field properties in the VKF supersonic/hypersonic wind

tunnels. This experimental, phase of the program will be used to providethe data needed to identify the particulate concentration and size dis-

tribution in the tunnel flow. Subsequently, this information concerningthe tunnel flow particulate characteristics Will determine the feasibility

of making conventional laser velocimeter measurements in the VKF windtunnels without "seeding" the flow.

Therefore, the primary objective of this test program was to obtain

laser-Mie scattering measurements in Tunnel B which will be used to defineflow field particulate concentration and size distribution. In an attempt

to fully utilize this tunnel entry and the. effort expended to install the

laser optical systems, the test objectives were expanded to make the follow-ing measurements and laser scattering measurement applications. Using thelaser Raman scattering system, measurements were obtained for use in defining

the local number density (nitrogen molecules per cu. cm.) in the free stream

and downstream of the bow wave of a blunt 5-deg cone. Using this same laser

scattering system, the effects of tunnel humidity on flow field measurementswere examined. And finally, using a Fabry-Perot interferometer system, thefeasibility of making velocity measurements based on a direct Doppler shift

measurement, in place of the more conventional laser velocimeter technique

requiring tunnel flow seeding, was tested. In summary, the test objectivesincluded an evaluation of the test section flow properties and the application

of various scattering measurement techniques.

These tests were conducted in Tunnel B at Mach Number 8 over the

.Reynolds number range of 0.5 to 3.0 million per foot. Measurements were

obtained with and without the dryers in the wind tunnel circuit whichproduced a maximum (humidity) dew point of nominally 30°F and a minimum

(humidity) frost point of -60°F. The pressure distribution on a blunt5-deg cone (the VKF standard calibration body) was used to monitor thef tunnel Mach number.

4

The observation volume of the laser scattering optics was positionedon the tunnel centerline in the center of the test section. With the modelinjected, this observation volume fell dowmstream of the blunt 5-deg conebow wave, but above the model surface. The location of the observation yolumerelative to the model was varied by changing the vertical position of themodel. At each test condition, a set of laser scattering data was tecordedwith the model retracted and injected into the flow. This produced testdata describing the flow field properties in the free-stream flow and thenin the local flow field above the blunt 5-deg cone.

This report describes the test apparatus, procedures, and data re-duction of the model surface pressures and the millivolt outputs of theoptical detectors.

Inquiries to obtain copies should be directed to AEDC/DOT, ArnoldAir Force Station, TN 37389. A microfilm record of the test results hasbeen retained in the VKF at AEDC.

2.0 APPARATUS

2.1 TEST FACILITY

Tunnel B (Fig. 1) is a closed circuit hypersonic wind tunnel with a50-in. diam test section. Two axisymmetric contoured nozzles are avail-able to provide Mach numbers of 6 and 8 and the tunnel may be operatedcontinuously over a range of pressure levels from 20 to 300 psia at Machnumber 6, and 50 to 900 psia at Mach number 8, with air supplied by theVKF main compressor plant. Stagnation temperatures sufficient to avoidair liquefaction in the test section (up to 1,350 R) are obtained throughthe use of a natural gas fired combustion heater. The entire tunnel(throat, nozzle, test section, and diffuser) is cooled by integral,external water jackets. The tunnel is equipped with a model injectionsystem, which allows removal of the model from the test section whilethe tunnel remains in operation. A descriptiof of the tunnel may befound in the Test Facilities Handbook (Ref. 1).

2.2 TEST ARTICLE

The blunt 5-deg cone pressure model shown in Fig. 2 is the standardcalibration body for the VKF. This cone which was designed and fabricatedin the VKF is nominally 30 in. long with a 6 in. base diam and a 0.375 in.radius nose. Sixty-eight (0.063 in. I.D.) pressure taps were installedin this stainless steel model. The pressure taps are located along fourlongitudinal rows spaced 90-deg apart with 17 equally spaced pressure tapsper row.

This calibration body was installed on a 12-deg prebend model sup-port system as shown in Fig. 3. Variations in the sector center ofrotation produces a systematic vertical displacement in the model axisrelative to the tunnel axis.

5

2.3 LASER SCATTERING SYSTEM

To accomplish the objective of particulate size distribution andconcentration measurements, an extensive optical diagnostics systemwas designed and installed in Tunnel B. The particular Mie scatteringmethod employed was developed by the PWT/AT Branch. The Mie scattering

instrumentation included a Spectra-Physics® argon ion laser with a beampower of approximately two watts at 514.5 nm, five detector units, anda laser receiver power meter as shown in Fig. 4. Each detector unitcontained two 1P28 photomultiplier tubes as detectors of the componentsof scattered and polarized laser light, and each unit was situated atone of five different windows for viewing the light scattered from theflow particles as they encountered laser light in the observation volume.The laser receiver power meter measured the beam transmission throughthe flow. Data were recorded by the VKF domputer. The pattern ofscattered light signal amplitudes, polarization states, beam transmission,and detector unit viewing angles uniquely determines the size distribu-tion and concentration, with the added potential of particulate materialidentification. Size specification accuracy increases with the numberof detectors. All these components were mounted on platforms supportedby the tunnel's two schlieren vibration-isolation support columns, whichare structures independent of the tunnel and located on each side of thetest section.

Components of the system located on the nonoperating side of thetunnel are shown in Fig. 5. A steel platform previously used for TunnelC work was modified and affixed to the vibration-isolation support. TheSpectra-Physics laser and three Mie scattering detector units were eachmounted on one of two levels of this platform. On the tunnel operatingside, two detector units and the laser power meter were mounted on anexisting table, and these components are shown in Fig. 6.

A view from within the tunnel test section of the optical componentslocated on the operating and nono~erating sides of the tunnel is qhownin Figs. 7 and 8, respectively. The detector unit mounted on top ofTunnel B is shown in Fig. 9a.

Additional optical instrumentation was installed for measurement ofthe nitrogen molecular number density. A cooled photomultiplier tube(Fig. 9b)-located above the tunnel observed Raman scattered radiationfrom the same observation volume through narrow bandpass and blockingfilters, and these signals were recorded by hand.

Finally, an optical system for measuring particulate velocities wasadded. A Coherent Radiation argon ion laser of approximately 3 wattsoutput of 514.5 rnm was mounted alongside the Spectra-Physics laser, anda complex optical system provided a primary and a reference beam fromthis laser, each intersecting at the observation volume. A Fabry-Perotinterferometer, associated optics, and an uncooled photomultiplier tubecompleted this velocity system; they were mounted on the operating sideas shown in Fig. 6d.

6

2.4 STANDARD TEST INSTRUMENTATION

The standard measuring and recording devices, and calibration methodsfor all the measured parameters other than those associated with the laserscattering system are listed in Table 1. This table also contains theestimated measurement uncertainties. The corresponding informationassociated with the measuring, recording, and calibration techniques forthe laser scattering systems will be documented by PWT/AT in their finalreport for ARO Project P32M-Oi. DECITO

3.0 TS ECITO

3.1 TEST CONDITIONS AND PROCEDURES

3.1.1 General

A summary of the nominal test conditions are given below.

M T ~psia TT OR Min Dew Pt U ft/sec PT2 psi RE 10-6 /ft

7.99 690 1350 -59 0 3878 5.89 3.07.98 460 1340 -530F 3864 3.95 2.07.95 232 1360 -520F 3891 2.03 1.07.90 116 1345 -50OF 3868 1.04 0.5

A test log showing all configurations and variables covered in thisprogram is presented in Table 2.

Unless specifically identified in Table 2, all data recorded withthe model injected into the tunnel flow were obtained with the modelcenter of rotation at 7.0 inches (see Fig. 3). When the column labeled"Cone in Tank" is checked, free stream laser scattering measurementswere recorded. In all other cases, the model was injected into thetunnel flow and either laser data or cone surface pressure measurementswere made as indicated in the test log, Table 2.

In the VKF continuous flow wind tunnels (A, B, C), the model ismounted on a sting support mechanism in an installation tank directlyunderneath the tunnel test section. The tank is separated from thetunnel by a pair of fairing doors and a safety door. When closed, thefairing doors, except for a slot for the pitch sector, cover the open-ing to the tank and the safety door seals the tunnel from the tank area.After the model is prepared for a data run, the personnel access doorto the installation tank is closed, the tank is vented to the tunnelflow, the safety and fairing doors are opened, the model is injectedinto the airstream, and the fairing doors are closed. After the dataare obtained, the model is retracted into the tank and the sequence isreversed with the tank being vented to atmosphere to allow access to themodel in preparation for the next run. The sequence is repeated for eachconfiguration change.

7

The free stream Mach number was confirmed on the basis of the pres-

sure distribution on the VKF standard calibration body, a blunt 5-degcone. These plotted pressure distributions are given in Fig. 10 and

include the theoretical'results used in confirming the free stream Mach

number. The theoretical results are based on the HVSL (three-dimensionalhypersonic viscous shock layer) code based on the work of Lubard and

Helliwell (see Refs. 2 and 3). This version of the HVSL provides an esti-mate of the induced pressure distribution produced on an unyawed bluntnose cone with laminar flow in a hypersonic stream.

3.1.2 Test Procedure

Basically the first shift as indicated in Table 2 was devoted to

defining the character of the flow when the tunnel dew point (humidity)was high (the order of 0 to +300 F). Cone surface pressure data weretaken at each new test condition. The laser scattering data wereobtained with the model in the tank to provide free stream results, andthen the model was injected into the tunnel flow to obtain similar results

in the local flow field over the model downstream of the model bow wave.

The final shift was devoted to obtaining similar data with thetunnel running in a very dry condition. In addition to obtaining laser

scattering data with and without the model injected into tunnel flow,'a

set of results was obtained as the model was moved relative to the laser-optics observation volume (Runs 27 to 30 in Table 2). This sequence oftests was run in an attempt to see if laser scattering measurements could

be used to detect the variations in the local static density in the flowfield of the blunt cone.

Preceding and following each tunnel shift, a set of air-off laserscattering data was recorded to provide additional calibration resultsfor the optical system.

3.1.3 Data Acquisition

The model surface pressure data were obtained by means of an pres-sure equilibrium technique described in Ref. 4. This required that eachpressure readout be scanned 40 times in one second intervals. Based onthe geometry of the pressure tubing from the model to the transducer,the nominal temperature of the air in the tubing, and the pressure-timehistory, the equilibrium pressure at the model surface could be defined.

The laser scattering results consisted of the millivolt output fromthe 10 photomultiplier detectors, the LILM, the LRPM, and the nitrogenconcentration output TOUT. Except for TOUT, the outputs were scanned300 times at equal time intervals of 0.03 seconds. All other measurementswere scanned once for each data run.

3.2 DATA REDUCTION

Except for the laser scattering evaluations, all other data reductionprocedures were standard. The output from.the laser scattering systemwas converted to millivolts using the proper amplifier gains and scalefactors, namely

Millivolts = (0.61035/Gain)Reading

8

The sampled signal consisting of 300 points was summed and tabulated alongwith the average value. A tare value, obtained by blocking the laser beam,was obtained prior to each data point. The tare value also consisted of300 sampled points which were summed and averaged. The tabulated resultsconsist of the tare value, the data point, and the difference between andtare and data point.

3.3 MEASUREMENT UNCERTAINTY

In general, instrumentation calibrations and data uncertainty esti-mates were made using methods recognized by the National Bureau ofStandards (NBS) and described in Ref. 5. Measurement uncertainty is acombination of bias and standard deviation defined as:

U - ±(B + t9 5)

where B is the bias limit, S is the sample standard deviation, and t 5 is

the 95th percentile point for the two-tailed Student's "t" distributionwhich for degrees of freedom greater than 30 is 2.

Estimates of the data uncertainties for the standard tunnel measure-ments are presented in Table 1. The uncertainty estimates for the laserscattering outputs will be included in the final analysis of the resultsby PWT/AT.

The bias and standard deviations of the measured data were propa-gated through the standard data reduction in accordance with Ref. 5.The results are included in Table 1.

4.0 DATA PACKAGE PRESENTATION

The data package consists of two data formats, namely, the blunt5-deg cone surface pressure results and the tabulated laser scatteringmillivolt outputs. Examples of the two data formats are given inAppendix III.

9

REFERENCE

1. Test Facilities Handbook (Eleventh Edition). "von Karman Gas DynamicFacility, Vol. 3,' Arnold Engineering Development Center, June 1979.

2. Lubard, S. C. and Helliwell, W. S. "Calculation of the Flow on aCone at High Angle of Attack." R&D Associates RDA-TR-150, SantaMonica, CA, February 1970.

3. Mayne, Arloe W., Jr. "Calculation of the Laminar Viscous Shock Layeron a Blunt Biconic Body at Incidence to Supersonic and HypersonicFlow." AEDC-TR-76-123, December 1976.

4. Brown, D. L. "Predicting Equilibrium P4ressures from Transient PressureData." Aerospace Research Laboratories ARL 65-7, January 1965.

5. Thompson, J. W. and Abernethy, R. B. et al. "Handbook Uncertainty inGas Turbine Measurements." AEDC-TR-73-5 (AD755356), February 1973.

10

L ____________

APPENDIX I

ILLUSTRATIONS

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TABLES

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DATA PACKAGE FORMATS

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