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NASA Technical Memorandum 84500 PRELIMINARY ANALYSIS OF STS-3 ENTRY DATA FOR THE ORBITER WINDWARD CENTERLINE David A. Throckmorton, H. Harris Hamilton II, and E. Vincent Zoby June 1982 NI\SI\ National Aeronautics and Space Administration Langley Research Center Hampton, Virginia23665 JOHN F. KENNEDY SPACE DOCUMENTS DEPARTMENT J8RAII,' REFERENCE COpy JON 2S 1982 https://ntrs.nasa.gov/search.jsp?R=19820020699 2018-07-29T02:30:29+00:00Z

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NASA Technical Memorandum 84500

PRELIMINARY ANALYSIS OF STS-3 ENTRY

HEAT~TRANSFER DATA FOR THEORBITER WINDWARD CENTERLINE

David A. Throckmorton,

H. Harris Hamilton II,and E. Vincent Zoby

June 1982

NI\SI\National Aeronautics andSpace Administration

Langley Research CenterHampton, Virginia23665

JOHN F. KENNEDY SPACE C£NTEJf(L~DOCUMENTS DEPARTMENT J8RAII,'REFERENCE COpy JON 2 S1982

https://ntrs.nasa.gov/search.jsp?R=19820020699 2018-07-29T02:30:29+00:00Z

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PRELIMINARY ANALYSIS OF STS-3 ENTRY HEAT-TRANSFER DATAFOR THE ORBITER WINDWARD CENTERLI~E

David A. Throckmorton, H. Harris Hamilton II,and E. Vincent Zoby

SUMMARY

A preliminary analysis of heat-transfer data on the Space ShuttleOrbiter windward centerline for the STS-3 mission entry is presented.The paper includes temperature-time history plots for each measurementlocation, and tabulated wall-temperature and convective heating-ratedata at 21 selected trajectory points. The STS-3 flight data are alsocompared with the predictions of two appproximate methods forcomputing convective heat-transfer rates in equilibrium air. Thepaper is intended to provide the technical community with early accessto a wide range of orbiter heat-transfer data.

INTRODUCTION

Temperature measurements obtained at the aerodynamic surface ofthe orbiter's thermal protection system (TPS) provide fordetermination of the aerothermodynamic environment to which theorbiter is subjected during entry from Earth orbit. The measuredtemperatures are used in a rigorous analysis of heat conductionwithin, and reradiation from, the TPS in order to determine convectiveheat-transfer rates. Convective heating-rate data for the orbiter'swindward centerline from the STS-3 mission entry are presented. Theflight data are compared with the results of two approximate methodsfor computing convective heat-transfer rates.

SYMBOLS AND ACRONYMS

DFI

h

TPS

development flight instrumentation

altitude

free-stream Mach number

free-stream pressure

convective heat-transfer rate

thermal protection system

TPS surface temperature

free-stream temperature

x/L

Poo

non-dimensional body length (L=32.89 m)

free-stream velocity

angle-of-attack

free-stream density

DATA SOURCE

2

During the orbital flight test missions, the orbiter has onboardan instrumentation system referred to as the development flightinstrumentation (DFI). The OFI is comprised of over 4500 sensors,associated data-handling electronics, and recorder, which provide datato enable postflight certification of orbiter subsystems design.Included among the OF! are measurements of the orbiter's aerodynamicsurface temperature at over 200 surface locations. These measurementsare obtained from thermocouples mounted within the thermal protectionsystem, in thermal contact with the aerodynamic surface coating.Sixteen of these thermocouples are located along the vehicle'swindward centerline (fig. 1). DFI thermal data are recorded once eachsecond throughout the entry time period. The measuredtemperature-time histories provide for determination of surface heat­transfer rates.

CONVECTIVE HEATING-RATE DETERMINATION

The measured time-histories of surface temperature are smoothedand subjected to an interactive review proce~s to assure that thesmoothed data provide an accurate representation of the rawtemperature data. An inverse, one-dimensional, transient analysis ofheat conduction within the TPS, and reradiation from the TPS surface,is used to determine convective heat-transfer rates (ref. 1). Theuncertainty of heating rates determined by this method has beenassessed (ref. 1) to be less than ~ 10 percent.

ANALYTICAL TECHNIQUES

The approximate heating method of Zoby (ref. 2) uses a rapidinviscid flow-field procedure, laminar and turbulent heating equationswhich can be computed for constant or variable-entroPY edgeconditions, and equilibrium-air correlations~ The flow environmentalong the windward centerline of the orbiter is approximated by usingan equivalent axisymmetric body. Resulting heating-rate calculationshave been validated for both laminar and turbulent flow conditions bycomparison with experimental ground-test data and results of morerigorous predictions (refs. 3 and 4) at shuttle flight designconditions. It ha~previously been used in the analysis of orbiterentry heating data (refs. 5 and 6).

The approximate heating method of Hamilton (ref. 7) is based on a"local infinite swept cylinder analysis" which can be used tocalculate both laminar and turbulent heating rates on the windwardside of the orbiter. The method includes both equilibrium-airthermodynamic properties and variable boundary-layer-edge entropy.It has been shown to be in good agreement with wind-tunnel data, andhas also been previously used in the analysis of orbiter entry heatingdata (ref. 7).

STS-3 RESULTS

Temperature Data

Smoothed temperature-time histories are shown in figure 2. Themeasurement location at x/L = 0.285 is part of an experiment (ref. 8)to investigate heating within gaps between TPS tiles.' Data are notpresented for the measurements at x/L = 0.297 and 0.402 as thesemeasurements were part of an experiment (ref. 9) to investigate thecatalytic efficiency of the TPS surface coating material. Data arepresented, however, for a measurement which is located at x/L = 0.401,but 1.14 meters off of the plane of symmetry. No data are presentedfor the measurements located at x/L = 0.691 and 0.946, as theseinstruments did not operate properly on STS-3.

Heat-Transfer Data

Windward centerline convective heat-transfer data, determined bythe method of reference 1, are tabulated in Table I for 21 trajectorypoints. These trajectory points span the entire portion of the entrywhich is- of aerothermodynamic interest. The first points are prior topeak aerodynamic heating, and the last point is after boundary-layertransition has occurred over 90 percent of the vehicle1s windwardcenterline.

Flight Environment Definition - Table I also contains informationwhich describes the flight environment at each trajectory point.Determination of the flight environment parameters was accomplishedthrough a process of reconstruction of the orbiter entry trajectory,modeling of the atmosphere on the day of entry, and correlation ofthese two data sets to provide an analytically~consistent definitionof the entry flight environment. The vehicle state parameters ofa1t i tude, veloci ty, and angl e of attack were determined through thetrajectory reconstruction process of reference 10. Free-streamtemperature was determined by the process of reference 11, whichcombines atmospheric modeling with direct measurement of atmosphericprofiles on the day of entry. Atmospheric density was determinedthrough a correlation of local surface pressure coefficient withfree-stream dynamic pressure. The correlation function was generatedusing both wind-tunnel and flow-field computational results.Aerodynamic surface pressure was measured at a point on the windward

3

4

centerline at x/L = 0.025. The measured pressure was input to thecorrelation function in order to determine dynamic pressure.*Consideration of the vehicle velocity then provided for thedetermination of the atmospheric density. Free-stream pressure wasdetermined by applying the gas law to the temperature and densitydata. The flight environment information contained in Table I wasused as input to the analytical methods in generating the flightpredictions to be discussed in the following section.

Heat-Transfer Distributions

Flight-measured heat-transfer distributions at five trajectorypoints, along with the approximate equilibrium-chemistry predictionsof Hamilton and Zoby, are shown in figure 3. At time = 270 seconds,(fig. 3(a)), the flight data on the forward portion of the vehicleare as much as 35-percent lower than the equilibrium predictions;while on the aft portion of the vehicle, the flight data andpredictions are in relatively good agreement. The large disparitybetween prediction and flight data on the forward portion of thevehicle is attributed to nonequilibrium chemistry in the shock layerin flight.

At time:: 350 seconds (fig. 3(b», the comparison betweenpredictions and flight data is similar to that for the previous time.However t note that the data point at x/L :: 0.166 is substantiallyhigher than the surrounding data. The TPS tile which contains thismeasurement was previously coated with a highly catalytic material onSTS-2, as part of the experiment of reference 9. Although the coatingwas cleaned from this tile prior to STS-3, the STS-3 data indicatethat the catalytic efficiency of the surface of this tile remainsgreater than that of the surrounding baseline instrumented tiles.

In figure 3(c), time:: 640 seconds, heating to the forwardportion of the vehicle has increased substantially from the levelsobserved at the previous time, and downstream of x/L :: 0.10,approaches the levels of the equilibrium predictions. The increasedheating is probably the result of increased catalytic efficiency ofthe tile surface due to surface contamination--the contaminationresulting from the melting of an acoustic-sensor cover at thislocation and deposition of melted material on the surface of thethermally-instrumented tiles downstream. Acoustic sensors are locatedon the vehicle centerline at x/L = 0.106 and x/L :: 0.204. Postflightvisual inspection of the TPS confirms that these sensors are a sourceof TPS contamination. The apparent occurrence, in time, of thecont ami nat ion 1s evidenced by a sudden and si gn1 f1cant temperature'~

rise which occurs at a time of 520 seconds (figs. 2(e) and (g». Thisphenomenon was previously observed at several centerline measurementlocations on STS-2 (ref. 6).

*The correlation of local pressure coefficient with free-streamdynamic pressure was performed by R. C. Blanchard of the LangleyResearch Center and is to be described in a future publication.

r:

At the later times (figs. 3(d) and (e)), the agreement betweenflight data and equilibrium-chemistry predictions becomesprogressively better. It should be noted, however, that on STS-2 atapproximately the same altitude/velocity/angle-of-attack condition asthat of figure 3(e), nonequilibrium predictions indicate thatsignificant nonequilibrium effects should still be evident in theheat-transfer data (ref. 12). Also, on STS-2, the coated tiles of theCatalytic Surface Experiment (ref. 13) provided evidence ofnonequilibrium chemistry effects in the boundary layer at similarflight conditions.

CONCLUDING REMARKS

Apreliminary analysis of orbiter windward-centerlineheat-transfer data from the STS-3 mission entry is presented. Theflight data were compared with the predictions of two appproximatemethods for computing convective heat-transfer rates in air inchemical equilibrium. The comparisons indicate that at altitudesgreater than 60 kilometers, flight heat-transfer rates aresignificantly influenced by nonequilibrium chemistry effects. Ataltitudes below 60 kilometers, the flight data and equilibriumchemistry predictions are in good agreement. However, even at theseconditions, other computations and experiment indicate thatsignificant nonequilibrium chemistry effects should still be evident.

REFERENCES

1. Throckmorton, D. A.: Benchmark Aerodynamic Heat Transfer Datafrom the First Flight of the Space Shuttle Orbiter. AIAA Paper82-0003, January 1982.

2. Zoby, E. V.; Moss, J. N.; and Sutton, K.: Approximate ConvectiveHeating Equations for Hypersonic Flows. Journal of Spacecraftand Rockets, vol.18, no. 1, January 1981.

3. Rakich, J. V.; and Lanfranco, M. J.: Numerical Computation ofSpace Shuttle Laminar Heating and Surface Streamlines. Journalof Spacecraft and Rockets, vol. 14, no.5, May 1977.

4. Goodrich, W. D.; Li, C. P.; Houston, C. K.; Chiu, P. B.; andOlmedo, L.: Numerical Computations of Orbiter Flowfields andLaminar Heating Rates. Journal of Spacecraft and Rockets,vol. 14, no. 5, May 1977.

5. Zoby, E. V.: Comparisons of Free-flight Experimental andPredicted Heating Rates for the Space Shuttle. AlAA Paper82-0002, January 1982.

6. Zoby, E. V.: Analysis of STS-2 Experimental Heating Rates andTransition Data. AlAA Paper 82-0822, June 1982.

5

6

7. Hamilton, H. H. II: Approximate Method of Predicting Heating onthe Windward Side of Space Shuttle Orbiter and Comparisons toFlight Data. AIAA Paper 82-0823, June 1982.

8. Pitts, W. C.: Flight Measurements of Tile Gap Heating on theSpace Shuttle. AlAA Paper 82-0840, June 1982.

9. Stewart, O. A.; and Rak lch , J. V.: Catalytic Surface EffectsExperiment on Space Shuttle. AIAA Paper 81-1143, June 1981.

10. Compton, H. R.; Findlay, J. T.; Kelly, G. M.; and Heck, M.l.:Shuttle (STS-1) Entry Trajectory Reconstruction. AIAA Paper81-2459, November 1981.

11. Price, J. M.; and Blanchard, R. c.: Determination of AtmosphericProperties for STS-l Aerothermodyn~nic Investigations. AIAAPaper 81-2430, November 1981.

12. Shinn, J. l.; Moss, J. N.; and Simmonds, A. l.: Viscous ShockLayer Heating Analysis for the Shuttle Windward Plane withSurface Finite Catalytic Recombination Rates. AIAA Paper82-0842, June 1982.

13. Rakich, J. V.; and Stewart, D. A.: Results of a FlightExperiment on the. Catalytic Efficiency of the Space ShuttleHeat Shield. AIAA Paper B2~0944, June 1982.

Table I - 5T5-3 Windward Centerline Heat Transfer

Time = 225 seesh = 88.1 kmu~ = 7.44 km/seea = 40.1 degrees

M~ = 26.7p~ = 0.28 N/m 2

Tee = 193 Kp~ = 4.96 X 10- 6 kg/m 3

x/L Tw (K) qe (kW/m 2 )

0.025 1055 77.50.098 884 40.10.140 838 33.20.166 829 32.60.194 767 26.20.255 791 27.00.285 770 25.40.401 764 23.90.497 732 22.00.592 741 22.00.795 692 18.00.894 656 14.50.986 572 9.0

7

Table I - Continued.

Time = 245 seesh = 85.3 kmUoo = 7.47 km/seea = 39.4 degrees

Moo = 26.9Poo = 0.43 N/m 2

Too = 192 KPoo = 7.78 x 10- 6 kg/m 3

8

x/L

0.0250.0980.1400.1660.1940.2550.2850.4010.4970.5920.7'950.8940.986

TW

(K)

1136963909901858868864831822815763726642

qc (kW/m 2)

98.251.542.039.634.935.936.229.430.528.723.719.814.0

Table I - Continued.

Time = 270 seesh = 82.2 kmu~ = 7.52 km/seea = 39.5 degrees

M~ = 27.1p~ = 0.70 N/m 2

Tee = 192 Kp~ = 1.28 X 10- 5 kg/m 3

x/L Tw (K) qc (kW/m 2)

0.025 1203 121.0.098 1027 64.20.140 974 51.90.166 957 49.00.194 934 45.60.255 938 46.50.285 949 46.90.401 902 40.50.497 902 40.20.592 883 36.20.795 851 , 33.90.894 799 26.70.986 715 19.2

9

Table I - Continued.

Time = 300 seesh = 79.0 kmu~ = 7.50 km/seea = 41.0 degrees

Moo = 26.9p~ = 1.17 N/m 2

Tee = 194 KPw = 2.09 X 10- 5 kg/m 3

10

x/L

0.0250.0980.1400.1660.1940.2550.2850.4010.4970.5920.7950.8940.986

Tw (K)

126610821039103710011008

979972962938941890686

qc (kW/m 2)

144.76.866.567.058.259.552.752.149.845.547.439.4to.7

Table I - Continued.

Time = 350 seesh = 76.2 kmUoo =7.40 km/seea = 39.6 degrees

Moo = 26.2Pm = 1.90 N/m 2

Too = 199 KPm = 3.32 X 10- 5 kg/m 3

x/L TW

(K) qe (kW/m 2)

0.025 1324 168.0.098 1124 86.70.140 1108 81.70.166 1193 112.0.194 1051 67.30.255 1048 66.20.285 1019 59.40.401 1016 58.60.497 1009 57.30.592 1002 56.50.795 1017 59.10.894 971 50.20.986 647 10.4

11

Table I - Continued.

Time = 415 seesh = 74.7 kmuoo = 7.26 km/seca = 40.1 degrees

Moo = 25.5Pm = 2.40 Nfm 2

Too =202 KPoo = 4.14 X 10- 5 kg/m3

12

x/L Tw (K) Qc (kW/m 2)

0.025 1345 176.0.098 1147 93.30.140 1162 98.40.166 1233 123.0.194 1077 73.20.255 1077 72.70.285 1048 65.70.401 1043 64.70.497 1034 62.40.592 1057 6fL20.795 1051 67.00.894 996 54.00.986 703 14.6

Table I - Continued.

Time = 495 seesh = 73.1 kmu~ = 7.05 km/seea = 39.6 degrees

M~ = 24.5p~ = 3.22 N/m 2

T~ = 207 Kp~ = 5.42 X 10- 5 kg/m 3

x/L T (K) q (kW/m 2)w e

0.025 1357 182.0.098 1165 98.20.140 1194 109.0.166 1217 116.0.194 1105 80.10.255 1100 79.00.285 1082 73.90.401 1056 67.20.497 1052 66.50.592 1069 70.40.795 1069 71.00.894 1002 54.70.986 713 14.5

13

Table I ... Continued.

Time = 640 seesh = 70.1 kmu~ = 6.57 km/seea = 40.1 degrees

M~ = 22.3p~ ;;; 51OlO Nlm 2

Too = 217 KPoo = 8.19 X 10... 5 kg/m3

14

x/L

0.0250.0980.1400.. 1660 .. 1940.2550.2850.4010.49.70.5920.7960.8940.986

Tw (K)

137811891214120911591130111410761058105710651002

664

qc (kW/m 2)

192.106.115.113.95.685.981.97L.666.566.168.354.110.8

Table I - Continued.

Time = 745 seesh = 67.0 kmu~ = 6.09 km/seea = 39.9 degrees

Moo = 19.9Poo = 8.25 N/m 2

Too = 233 KPoo = 1.23 X 10-4 kg/m 3

x/L Tw (K) q (kW/m 2 )e

0.025 1403 205.0.098 1211 114.0.140 1200 109.0.166 1192 106.0.194 1136 87.70.255 1113 81.30.285 1096 76.20.401 1064 67.90.497 1038 61.70.592 1033 60.40.795 1041 62.20.894 988 51.10.986 673 11.4

15

Tab le I-Cant; fltfetl.

Time = 825 seesh =64.0 kmuoo = 5 .;6;6 km/seca = 39.3 degrees

Moo = 17.9Poo = 13.5 N/m2

TOD::: 24'9 K':>00 = 1.89 x 10- It kg/m3

1'6

x/t,

'0.0,250.098'0.1,4'00.1660.lr9'4

'0.25'5'O.2~'S'O.,4l01'0.'4'910.5'92O.7'gS0.89'4O.9~6

T (K)w

142412~2

11:87111811161'0971'(}8111()4a11(l21170091'()'28

98,2664

21r.nr.104.1'01.SJL47$.971.8~3,. 't$,,,'5'$:_.,.1'$9.1_9.fi10;,8

Table I - Continued.

Time = 920 seesh = 60.8 kmu~ = 4.98 km/seea = 43.0 degrees

M~ = 15.4p~ = 20.9 N/m 2

Tee = 262 Kp~ = 2.77 X 10- 4 kg/m 3

x/L T (K) qe (kW/m 2)w

0.025 1384 192.0.098 1183 103.0.140 1147 90.50.166 1145 89.90.194 1082 72.00.255 1052 64.40.285 1048 63.70.401 1016 56.20.497 982 48.90.592 955 43.90.795 981 48.90.894 963 45.70.986 662 9.2

17

Table I - Conti nued ,

Time = 960 seesh = 57.8 kmUoo = 4.61 kmls~ca = 40.9 degr,e.es

Moo = 14.,0Poo = 31.4 N/m 2

Too = 269 KPoo =4.06 x 10- 4 kg/m 3

18

x/L

0.0,250.09·80.14:0o.iss0.1940.2,55Q .2;13:5O.tWl0,.4'9,70.5'2o. 7'~'5

0.894O.9ati

Tw (K)

1357116,01121I1t810581023102,39899,'6:292393694463~

q (k:W./im 2)c

171..94.'882.•481...60,5 ..•.756,.251,.155.@,.l44~9

3$.l4(t~2

42.2;$,.1

Table I - Continued.

Time = 1015 seesh = 55.0 kmu~ = 4.07 km/seea = 39.6 degrees

M~ = 12.3p~ = 45.3 N/m 2

T~ = 272 Kp~ = 5.80 X 10-4 kg/m 3

x/L Tw

(K) qe (kW/m 2)

0.025 1295 145.0.098 1102 76.70.140 1066 67.00.166 1054 62.50.194 1007 53.50.255 967 42.80.285 967 45.50.401 938 40.30.497 918 37.10.592- 877 30.80.795 874 29.50.894 889 31.80.986 594 5.8

19

Table I - Continued.

Time = 1080 seesh = 51.8 kmu~ = 3.44 km/seea = 38.9 degrees

Moo = 10.4p~ = 65.4 N/m 2

Too = 273 Kp~ = 8.36 X 10- 4 kg/m 3

20

x/L

0.0250.0980.1400.1660.1940.2550.2850.4010.4970.5920.7950.8940.986

12041021978965930895901875865807798799574

Qc (kW/m 2)

107.54.845.44,2.937.232.032.829.429.120.219.119.35.3

Table I - Continued.

Time = 1100 seesh = 50.3 kmu~ = 3.25 km/seea = 38.0 degrees

M~ = 9.82Pee = 86. 7 N/m2

Teo = 272 Kp~ = 1.11 X 10- 3 kg/m 3

x/L Tw (K) qe (kW/m 2 )

0.025 1178 97.10.098 998 49.30.140 951 39.80.166 937 37.40.194 910 33.9-0.255 877 30.30.285 884 30.30.401 856 26.10.497 845 26.20.592 788 18.30.795 781 17.10.894 77t 16.70.986 588 6.7

21

Table I - Continued.

Time = 1120 seesh = 48.8 kmuoo = 3.05 km/seca = 36.4 degrees

Moo = 9.3Pc» = 94.5 Nlm 2

Too = 270 KPoo = 1.19 X 10-3 kg/m 3

22

x/L

0.0250.0980.1400.1660.1940.2550.2850.4010.4970.5920.7950.8940.986

T (K)w

1155975923907890859864839830766811818777

qc (kW/m 2)

89.845.235.432.632.126.827.625.423.517.134.134.746.2

Table I - Continued.

Time = 1145 seesh = 47.3 kmUoo = 2.82 km/seea = 33.6 degrees

Moo = 8.6Poo = 114 N/m 2

Too = 268 KPoo = 1.48 X 10- 3 kg/m 3

x/L T (K) qe (kW/m 2 )w

0.025 1113 75.70.098 940 38.20.140 880 28.70.166 865 26.50.194 860 26.80.255 827 21.80.285 831 23.00.401 807 20.20.497 802 18.40.592 742 14.80.795 1021 51.10.894 967 40.10.986 953 47.8

23

Table I - Continued.

Time = 1180 seesh = 45.8 kmu~ = 2.51 km/seea = 33.3 degrees

M~ = 7.7PQ) = 136 N/m 2

TCXl = 266 KpO) = 1.79 X 10- 3 kg/m 3

24

x/L T (K) qc (kW/m 2)w

0.025 1042 56.20.098 881 28.30.140 824 20.60.166 810 19.70.194 813 20.00.255 772 16.40.285 786 17.50.401 762 15.70.497 756 15.30.592 975 56.30.795 1007 53.50.894 944 41.20.986 911 36 .. 5

Table I - Continued.

Time = 1220 seesh = 42.8 kmu~ = 2.21 km/seea = 29.6 degrees

M~ = 6.8p~ = 203 N/m 2

Tee = 259 Kp~ = 2.72 X 10- 3 kg/m 3

x/L Tw (K) qc (kW/m 2)

0.025 972 41.60.098 820 20.50.140 941 42.10.166 936 39.80.194 929 39.60.255 924 39.10.285 924 39.30.401 928 40.10.497 937 41.20.592 940 40.40.795 947 40.90.894 889 31.60.986 858 27.8

25

Table I - Continued.

Time = 1260 seesh = 39.6 kmu~ = 1.91 km/seea = 26.1 degrees

Moo = 6.01Poo = 306 N/m 2

Tco = 252 KPoo = 4.23 X 10-3 kg/m 3

26

x/L

0.0250.0980.1400.1660.1940.2550.2850.4010.4970.5920.7950~894

()~980

Tw (K)

910770899888884878878880886882886833803

qc (kW/m 2)

30.916,632.330.630.529,429.530.031.030,230.523.620.8

Table I - Concluded.

Time = 1300 secsh = 36.5 kmu~ = 1.63 km/seca = 22.7 degrees

M~ = 5.2p~ = 468 N/m 2

T~ = 244 Kp~ = 6.70 X 10- 3 kg/m 3

x/L Tw (K) qc (kW/m 2 )

0.025 844 21.10.098 845 26.80.140 835 22.40.166 823 20.80.194 820 21.10.255 811 20.00.285 811 19.80.401 816 21.00.497 817 20.80.592 811 2&.20.795 817 21.00.894 772 16.20.986 748 14.9

27

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Figure 1. - Windward centerline surface temperature measurement locations.

1600800 1200TIME (SECONDS)

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1. Report No.

NASA TM-84500I 2. Government Accession No. 3. Recipient's Catalog No.

4. Title and Subtitle

Preliminary Analysis of STS-3 Entry Heat-TransferData for the Orbiter Windward Centerline

5. Report DateJune 1982

6. Performing Organization Code

506-51-33-018. Performing Organization Report No.7. Authorfs)

David A. Throckmorton, H. Harris Hamilton II,and E. Vincent Zoby

~------------------------------i 10. Work Unit No.9. Performing Organization Name and Address

NASA Langley Research CenterHampton, VA 23365

11. Contract or Grant No.

13. Type of Report and Period Covered

12. Sponsoring Agency Name and Address

National Aeronautics and Space AdministrationWashington, DC 20546

Technical Memorandum14. Sponsoring Agency Code

15. Supplementary Notes

16. Abstract

A preliminary analysis of heat-transfer data on the Space Shuttle Orbiterwindward centerline for the STS-3 mission entry is presented. The paperincludes temperature-time history plots for each measurement location, andtabulated wall-temperature and convective heating-rate data at 21 selectedtrajectory points. The 5T5-3 flight data are also compared with thepredictions of two approximate methods for computing convective heat-transferrates in equilibrium air. The paper is intended to provide the technicalconmunity with early access to a wide range of orbiter heat-transfer data.

17. Key Words (Suggested by Author(s)) 18. Distribution Statement

Space ShuttleAerodynamic heatingAerothermodynamics

Unclassified - UnlimitedSubject Category 34

19. Security C1assif. (of this report}

Unclassified20. Security Classif. (of this page)

Unclassified21. No. of Pages

, 4822. Price

A03

N-30S For sale by the National Technical Information Service, Springfield. Virginia 22161