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NREL's S821 Airfoil (s821-nr) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NREL's S821 Airfoil (s821-nr)
Reynolds number: 200,000
Max Cl/Cd: 51.07 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s821-nr-200000-n5.txt
Download as CSV file: xf-s821-nr-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S821 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.1334   0.09492   0.08917  -0.0597   0.9680   0.1870
  -7.000  -0.6132   0.03174   0.02434  -0.0879   0.9111   0.2191
  -6.750  -0.5989   0.03064   0.02324  -0.0878   0.9008   0.2200
  -6.500  -0.5739   0.02971   0.02236  -0.0889   0.8936   0.2209
  -6.250  -0.5532   0.02866   0.02131  -0.0898   0.8847   0.2218
  -6.000  -0.5287   0.02760   0.02024  -0.0914   0.8762   0.2229
  -5.750  -0.4942   0.02656   0.01918  -0.0945   0.8715   0.2241
  -5.500  -0.4723   0.02564   0.01822  -0.0953   0.8600   0.2252
  -5.250  -0.4363   0.02466   0.01719  -0.0984   0.8540   0.2265
  -5.000  -0.4032   0.02376   0.01622  -0.1008   0.8456   0.2278
  -4.750  -0.3671   0.02290   0.01528  -0.1037   0.8367   0.2291
  -4.500  -0.3194   0.02202   0.01430  -0.1087   0.8303   0.2306
  -4.250  -0.2841   0.02133   0.01350  -0.1112   0.8183   0.2318
  -4.000  -0.2379   0.02070   0.01281  -0.1153   0.8091   0.2331
  -3.750  -0.2045   0.02034   0.01247  -0.1167   0.7958   0.2343
  -3.500  -0.1650   0.02000   0.01212  -0.1192   0.7839   0.2358
  -3.250  -0.1339   0.01970   0.01180  -0.1202   0.7699   0.2371
  -3.000  -0.1019   0.01941   0.01146  -0.1213   0.7568   0.2386
  -2.750  -0.0713   0.01913   0.01112  -0.1222   0.7435   0.2401
  -2.500  -0.0430   0.01885   0.01079  -0.1226   0.7305   0.2415
  -2.250  -0.0131   0.01859   0.01042  -0.1233   0.7177   0.2431
  -2.000   0.0139   0.01833   0.01010  -0.1235   0.7051   0.2446
  -1.750   0.0433   0.01810   0.00976  -0.1241   0.6938   0.2460
  -1.500   0.0698   0.01788   0.00954  -0.1240   0.6821   0.2474
  -1.250   0.0980   0.01774   0.00938  -0.1241   0.6707   0.2489
  -1.000   0.1246   0.01761   0.00928  -0.1240   0.6591   0.2504
  -0.750   0.1528   0.01751   0.00915  -0.1241   0.6483   0.2522
  -0.500   0.1804   0.01740   0.00904  -0.1241   0.6382   0.2542
  -0.250   0.2083   0.01729   0.00890  -0.1241   0.6280   0.2563
   0.000   0.2366   0.01719   0.00875  -0.1242   0.6184   0.2585
   0.250   0.2643   0.01708   0.00859  -0.1242   0.6079   0.2604
   0.500   0.2926   0.01700   0.00846  -0.1243   0.5986   0.2623
   0.750   0.3198   0.01690   0.00845  -0.1241   0.5891   0.2642
   1.000   0.3478   0.01687   0.00842  -0.1240   0.5803   0.2663
   1.250   0.3760   0.01684   0.00840  -0.1240   0.5718   0.2686
   1.500   0.4037   0.01681   0.00838  -0.1239   0.5625   0.2710
   1.750   0.4321   0.01681   0.00832  -0.1239   0.5541   0.2737
   2.000   0.4603   0.01678   0.00829  -0.1238   0.5461   0.2765
   2.250   0.4881   0.01677   0.00832  -0.1237   0.5377   0.2792
   2.500   0.5163   0.01681   0.00838  -0.1236   0.5300   0.2820
   2.750   0.5439   0.01682   0.00846  -0.1234   0.5219   0.2850
   3.000   0.5717   0.01687   0.00850  -0.1232   0.5139   0.2883
   3.250   0.5995   0.01693   0.00853  -0.1230   0.5061   0.2916
   3.500   0.6263   0.01695   0.00858  -0.1226   0.4967   0.2946
   3.750   0.6528   0.01702   0.00867  -0.1221   0.4875   0.2976
   4.000   0.6791   0.01708   0.00879  -0.1216   0.4781   0.3008
   4.250   0.7048   0.01717   0.00889  -0.1210   0.4682   0.3044
   4.500   0.7307   0.01727   0.00898  -0.1204   0.4590   0.3084
   4.750   0.7561   0.01737   0.00908  -0.1197   0.4490   0.3121
   5.000   0.7811   0.01749   0.00924  -0.1189   0.4400   0.3159
   5.250   0.8057   0.01760   0.00942  -0.1181   0.4296   0.3199
   5.500   0.8292   0.01778   0.00956  -0.1171   0.4198   0.3242
   5.750   0.8531   0.01790   0.00971  -0.1161   0.4092   0.3284
   6.000   0.8746   0.01807   0.00987  -0.1147   0.3991   0.3320
   6.250   0.8972   0.01820   0.01010  -0.1135   0.3884   0.3359
   6.500   0.9171   0.01842   0.01032  -0.1119   0.3779   0.3401
   6.750   0.9384   0.01862   0.01055  -0.1105   0.3658   0.3449
   7.000   0.9581   0.01889   0.01078  -0.1089   0.3539   0.3494
   7.250   0.9771   0.01918   0.01112  -0.1072   0.3402   0.3536
   7.500   0.9964   0.01951   0.01149  -0.1056   0.3252   0.3583
   7.750   1.0141   0.01991   0.01187  -0.1038   0.3089   0.3631
   8.000   1.0300   0.02039   0.01229  -0.1018   0.2904   0.3679
   8.250   1.0442   0.02094   0.01280  -0.0996   0.2701   0.3723
   8.500   1.0565   0.02161   0.01342  -0.0973   0.2492   0.3766
   8.750   1.0672   0.02239   0.01413  -0.0948   0.2296   0.3814
   9.000   1.0777   0.02324   0.01490  -0.0924   0.2117   0.3863
   9.250   1.0882   0.02413   0.01571  -0.0902   0.1958   0.3911
   9.500   1.0990   0.02504   0.01662  -0.0880   0.1813   0.3956
   9.750   1.1096   0.02599   0.01758  -0.0860   0.1684   0.4004
  10.000   1.1196   0.02702   0.01859  -0.0840   0.1569   0.4056
  10.250   1.1292   0.02812   0.01967  -0.0821   0.1467   0.4108
  10.500   1.1377   0.02933   0.02087  -0.0802   0.1374   0.4154
  10.750   1.1470   0.03055   0.02213  -0.0786   0.1287   0.4204
  11.000   1.1560   0.03183   0.02345  -0.0770   0.1211   0.4258
  11.250   1.1634   0.03329   0.02491  -0.0755   0.1143   0.4312
  11.750   1.1796   0.03630   0.02801  -0.0730   0.1023   0.4414
  12.000   1.1860   0.03803   0.02978  -0.0718   0.0971   0.4469
  12.250   1.1938   0.03973   0.03154  -0.0709   0.0924   0.4528
  12.500   1.1992   0.04171   0.03353  -0.0700   0.0881   0.4584
  12.750   1.2066   0.04358   0.03549  -0.0693   0.0841   0.4636
  13.000   1.2116   0.04574   0.03772  -0.0687   0.0803   0.4691
  13.250   1.2179   0.04786   0.03992  -0.0683   0.0768   0.4754
  13.500   1.2226   0.05021   0.04230  -0.0679   0.0736   0.4816
  13.750   1.2273   0.05263   0.04481  -0.0677   0.0706   0.4873
  14.000   1.2324   0.05509   0.04736  -0.0676   0.0676   0.4935
  14.250   1.2350   0.05789   0.05022  -0.0677   0.0650   0.4997
  14.500   1.2401   0.06048   0.05289  -0.0678   0.0622   0.5064
  14.750   1.2427   0.06345   0.05594  -0.0681   0.0597   0.5123
  15.000   1.2464   0.06636   0.05895  -0.0685   0.0574   0.5192
  15.250   1.2494   0.06943   0.06210  -0.0690   0.0551   0.5265
  15.500   1.2502   0.07285   0.06558  -0.0697   0.0533   0.5328
  15.750   1.2541   0.07596   0.06882  -0.0703   0.0511   0.5399
  16.000   1.2557   0.07943   0.07238  -0.0712   0.0492   0.5474
  16.500   1.2587   0.08659   0.07973  -0.0733   0.0457   0.5623
  16.750   1.2595   0.09036   0.08359  -0.0745   0.0441   0.5706
  17.000   1.2584   0.09445   0.08774  -0.0760   0.0428   0.5782
  17.250   1.2605   0.09814   0.09157  -0.0773   0.0413   0.5864
  17.500   1.2613   0.10204   0.09558  -0.0788   0.0399   0.5955
  17.750   1.2602   0.10629   0.09992  -0.0806   0.0388   0.6039
  18.000   1.2598   0.11048   0.10420  -0.0824   0.0377   0.6134
  18.250   1.2609   0.11445   0.10830  -0.0841   0.0364   0.6237
  18.500   1.2606   0.11867   0.11263  -0.0861   0.0353   0.6341
  19.000   1.2580   0.12748   0.12162  -0.0905   0.0336   0.6564
  19.250   1.2589   0.13150   0.12578  -0.0925   0.0326   0.6697
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