Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NREL's S823 Airfoil (s823-nr) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NREL's S823 Airfoil (s823-nr)
Reynolds number: 500,000
Max Cl/Cd: 86.15 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s823-nr-500000.txt
Download as CSV file: xf-s823-nr-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S823 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -0.9106   0.08781   0.08334  -0.0593   1.0000   0.1153
 -16.000  -0.9270   0.08265   0.07807  -0.0614   1.0000   0.1159
 -15.750  -0.9276   0.08006   0.07547  -0.0621   1.0000   0.1178
 -15.500  -0.9277   0.07732   0.07272  -0.0629   1.0000   0.1187
 -15.250  -0.9263   0.07471   0.07012  -0.0639   1.0000   0.1202
 -15.000  -0.9289   0.07161   0.06700  -0.0650   1.0000   0.1212
 -14.750  -0.9329   0.06840   0.06374  -0.0661   1.0000   0.1221
 -14.500  -0.9366   0.06533   0.06062  -0.0670   1.0000   0.1229
 -14.250  -0.9419   0.06213   0.05736  -0.0680   1.0000   0.1239
 -14.000  -0.9466   0.05907   0.05425  -0.0689   1.0000   0.1247
 -13.750  -0.9507   0.05621   0.05133  -0.0695   1.0000   0.1253
 -13.500  -0.9545   0.05351   0.04855  -0.0700   1.0000   0.1259
 -13.250  -0.9598   0.05070   0.04568  -0.0705   1.0000   0.1267
 -13.000  -0.9642   0.04818   0.04309  -0.0707   1.0000   0.1272
 -12.750  -0.9691   0.04583   0.04069  -0.0708   1.0000   0.1277
 -12.500  -0.9735   0.04373   0.03853  -0.0704   1.0000   0.1281
 -12.250  -0.9804   0.04178   0.03653  -0.0693   1.0000   0.1287
 -12.000  -0.9879   0.04016   0.03489  -0.0674   1.0000   0.1299
 -11.750  -0.9979   0.03861   0.03334  -0.0651   1.0000   0.1305
 -11.500  -0.9790   0.03674   0.03146  -0.0682   0.9977   0.1319
 -11.250  -0.9540   0.03485   0.02955  -0.0725   0.9945   0.1332
 -11.000  -0.9278   0.03308   0.02775  -0.0768   0.9916   0.1345
 -10.750  -0.9038   0.03142   0.02605  -0.0801   0.9870   0.1353
 -10.500  -0.8761   0.02989   0.02448  -0.0839   0.9834   0.1360
 -10.250  -0.8454   0.02844   0.02297  -0.0880   0.9809   0.1368
 -10.000  -0.8257   0.02699   0.02147  -0.0899   0.9732   0.1374
  -9.750  -0.7963   0.02564   0.02007  -0.0935   0.9693   0.1381
  -9.500  -0.7764   0.02430   0.01868  -0.0952   0.9608   0.1389
  -9.250  -0.7483   0.02304   0.01736  -0.0981   0.9558   0.1396
  -9.000  -0.7274   0.02184   0.01611  -0.0996   0.9470   0.1401
  -8.750  -0.6961   0.02069   0.01490  -0.1027   0.9421   0.1407
  -8.500  -0.6606   0.01970   0.01384  -0.1062   0.9384   0.1413
  -8.250  -0.6333   0.01843   0.01254  -0.1088   0.9294   0.1431
  -8.000  -0.5920   0.01741   0.01152  -0.1134   0.9257   0.1453
  -7.750  -0.5567   0.01668   0.01078  -0.1163   0.9179   0.1470
  -7.500  -0.5171   0.01606   0.01012  -0.1198   0.9108   0.1488
  -7.250  -0.4825   0.01557   0.00958  -0.1220   0.9010   0.1508
  -7.000  -0.4461   0.01514   0.00908  -0.1244   0.8918   0.1526
  -6.750  -0.4179   0.01483   0.00870  -0.1251   0.8794   0.1541
  -6.500  -0.3902   0.01446   0.00826  -0.1257   0.8678   0.1561
  -6.250  -0.3636   0.01396   0.00775  -0.1264   0.8568   0.1596
  -6.000  -0.3382   0.01365   0.00741  -0.1265   0.8453   0.1624
  -5.750  -0.3116   0.01341   0.00714  -0.1267   0.8348   0.1655
  -5.250  -0.2584   0.01295   0.00657  -0.1269   0.8141   0.1717
  -5.000  -0.2316   0.01268   0.00629  -0.1271   0.8050   0.1760
  -4.750  -0.2047   0.01250   0.00609  -0.1271   0.7952   0.1800
  -4.500  -0.1771   0.01239   0.00592  -0.1272   0.7860   0.1834
  -4.250  -0.1501   0.01214   0.00567  -0.1273   0.7767   0.1881
  -4.000  -0.1228   0.01196   0.00550  -0.1274   0.7678   0.1927
  -3.750  -0.0947   0.01187   0.00536  -0.1276   0.7593   0.1970
  -3.500  -0.0671   0.01172   0.00520  -0.1276   0.7506   0.2015
  -3.250  -0.0391   0.01157   0.00505  -0.1278   0.7421   0.2066
  -3.000  -0.0111   0.01148   0.00495  -0.1279   0.7335   0.2114
  -2.750   0.0173   0.01141   0.00483  -0.1280   0.7255   0.2155
  -2.500   0.0453   0.01125   0.00471  -0.1281   0.7173   0.2207
  -2.250   0.0737   0.01119   0.00462  -0.1282   0.7092   0.2256
  -2.000   0.1022   0.01116   0.00455  -0.1282   0.7012   0.2296
  -1.750   0.1305   0.01102   0.00445  -0.1284   0.6933   0.2352
  -1.500   0.1591   0.01096   0.00439  -0.1285   0.6857   0.2404
  -1.250   0.1876   0.01095   0.00434  -0.1285   0.6777   0.2449
  -1.000   0.2163   0.01086   0.00427  -0.1287   0.6705   0.2505
  -0.750   0.2448   0.01080   0.00424  -0.1287   0.6626   0.2560
  -0.500   0.2736   0.01083   0.00420  -0.1288   0.6556   0.2609
  -0.250   0.3021   0.01073   0.00417  -0.1288   0.6480   0.2667
   0.000   0.3309   0.01073   0.00416  -0.1289   0.6410   0.2726
   0.250   0.3595   0.01073   0.00415  -0.1289   0.6337   0.2777
   0.500   0.3882   0.01067   0.00414  -0.1290   0.6266   0.2839
   0.750   0.4169   0.01070   0.00416  -0.1290   0.6199   0.2904
   1.000   0.4455   0.01067   0.00417  -0.1290   0.6127   0.2966
   1.250   0.4744   0.01072   0.00420  -0.1290   0.6063   0.3039
   1.500   0.5028   0.01072   0.00424  -0.1290   0.5994   0.3110
   1.750   0.5314   0.01072   0.00429  -0.1290   0.5928   0.3185
   2.000   0.5600   0.01080   0.00434  -0.1289   0.5864   0.3256
   2.250   0.5884   0.01077   0.00440  -0.1288   0.5795   0.3327
   2.500   0.6169   0.01086   0.00445  -0.1287   0.5729   0.3396
   2.750   0.6448   0.01084   0.00451  -0.1286   0.5656   0.3460
   3.000   0.6726   0.01089   0.00457  -0.1283   0.5580   0.3529
   3.250   0.7003   0.01095   0.00464  -0.1281   0.5504   0.3600
   3.500   0.7279   0.01098   0.00472  -0.1278   0.5428   0.3673
   3.750   0.7554   0.01106   0.00481  -0.1275   0.5353   0.3746
   4.000   0.7826   0.01109   0.00489  -0.1271   0.5272   0.3815
   4.250   0.8096   0.01118   0.00499  -0.1267   0.5193   0.3891
   4.500   0.8365   0.01123   0.00509  -0.1263   0.5108   0.3967
   4.750   0.8631   0.01133   0.00521  -0.1258   0.5028   0.4047
   5.000   0.8894   0.01140   0.00532  -0.1252   0.4937   0.4121
   5.250   0.9155   0.01150   0.00546  -0.1246   0.4849   0.4203
   5.500   0.9407   0.01161   0.00558  -0.1239   0.4749   0.4283
   5.750   0.9662   0.01171   0.00574  -0.1232   0.4646   0.4363
   6.000   0.9905   0.01186   0.00588  -0.1223   0.4540   0.4445
   6.250   1.0146   0.01199   0.00605  -0.1213   0.4418   0.4529
   6.500   1.0382   0.01215   0.00622  -0.1203   0.4287   0.4612
   6.750   1.0608   0.01233   0.00643  -0.1191   0.4145   0.4695
   7.000   1.0820   0.01256   0.00664  -0.1176   0.3981   0.4781
   7.250   1.1002   0.01281   0.00688  -0.1156   0.3791   0.4865
   7.500   1.1154   0.01316   0.00715  -0.1131   0.3583   0.4947
   7.750   1.1312   0.01354   0.00750  -0.1108   0.3357   0.5031
   8.000   1.1448   0.01407   0.00792  -0.1082   0.3106   0.5117
   8.250   1.1573   0.01466   0.00843  -0.1056   0.2831   0.5202
   8.500   1.1677   0.01538   0.00901  -0.1027   0.2546   0.5288
   8.750   1.1766   0.01617   0.00969  -0.0996   0.2277   0.5372
   9.000   1.1866   0.01695   0.01036  -0.0969   0.2036   0.5464
   9.250   1.1960   0.01776   0.01111  -0.0941   0.1833   0.5558
   9.500   1.2055   0.01861   0.01189  -0.0915   0.1655   0.5649
   9.750   1.2153   0.01946   0.01271  -0.0890   0.1497   0.5751
  10.000   1.2245   0.02038   0.01360  -0.0866   0.1350   0.5849
  10.500   1.2428   0.02236   0.01555  -0.0822   0.1105   0.6063
  10.750   1.2518   0.02342   0.01662  -0.0801   0.1001   0.6175
  11.000   1.2599   0.02460   0.01779  -0.0781   0.0908   0.6296
  11.250   1.2667   0.02591   0.01910  -0.0761   0.0820   0.6418
  11.500   1.2757   0.02713   0.02037  -0.0744   0.0746   0.6547
  11.750   1.2827   0.02854   0.02181  -0.0727   0.0680   0.6684
  12.000   1.2899   0.03000   0.02331  -0.0711   0.0620   0.6831
  12.250   1.2970   0.03152   0.02489  -0.0697   0.0568   0.6991
  12.500   1.3030   0.03318   0.02660  -0.0683   0.0520   0.7165
  12.750   1.3094   0.03487   0.02837  -0.0671   0.0478   0.7361
  13.000   1.3150   0.03665   0.03023  -0.0659   0.0440   0.7589
  13.250   1.3192   0.03857   0.03226  -0.0647   0.0407   0.7863
  13.500   1.3240   0.04037   0.03421  -0.0634   0.0378   0.8265
  13.750   1.3192   0.04220   0.03627  -0.0610   0.0353   1.0000
  14.000   1.3257   0.04431   0.03842  -0.0605   0.0329   1.0000
  14.250   1.3301   0.04669   0.04081  -0.0601   0.0306   1.0000
  14.500   1.3316   0.04943   0.04357  -0.0597   0.0286   1.0000
  14.750   1.3371   0.05181   0.04600  -0.0595   0.0268   1.0000
  15.000   1.3395   0.05459   0.04880  -0.0594   0.0252   1.0000
  15.250   1.3388   0.05782   0.05206  -0.0594   0.0238   1.0000
  15.500   1.3432   0.06054   0.05485  -0.0595   0.0224   1.0000
  15.750   1.3451   0.06360   0.05796  -0.0597   0.0213   1.0000
  16.000   1.3430   0.06724   0.06164  -0.0602   0.0203   1.0000
  16.250   1.3421   0.07084   0.06531  -0.0608   0.0194   1.0000
  16.500   1.3446   0.07406   0.06860  -0.0613   0.0186   1.0000
  16.750   1.3457   0.07751   0.07212  -0.0620   0.0178   1.0000
  17.000   1.3442   0.08141   0.07607  -0.0630   0.0171   1.0000
  17.250   1.3390   0.08592   0.08065  -0.0642   0.0165   1.0000
  17.500   1.3353   0.09030   0.08511  -0.0655   0.0159   1.0000
<< Back to NREL's S823 Airfoil (s823-nr)

Polar data table (+)

Polar graphs


<< Back to NREL's S823 Airfoil (s823-nr)