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NREL's S801 Airfoil (s801-nr) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NREL's S801 Airfoil (s801-nr)
Reynolds number: 200,000
Max Cl/Cd: 85.24 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s801-nr-200000.txt
Download as CSV file: xf-s801-nr-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S801 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2923   0.09120   0.08788  -0.0723   0.9785   0.0639
  -9.000  -0.3179   0.07834   0.07499  -0.0968   0.9626   0.0667
  -8.750  -0.3340   0.07015   0.06660  -0.1076   0.9487   0.0673
  -8.500  -0.2769   0.07141   0.06813  -0.0962   0.9540   0.0700
  -8.250  -0.2632   0.06631   0.06299  -0.1030   0.9482   0.0721
  -8.000  -0.2638   0.05985   0.05641  -0.1117   0.9363   0.0749
  -7.750  -0.2782   0.05150   0.04738  -0.1226   0.9229   0.0812
  -7.500  -0.2458   0.04811   0.04412  -0.1250   0.9208   0.0836
  -7.250  -0.2506   0.03589   0.03054  -0.1280   0.9087   0.0568
  -7.000  -0.2197   0.03045   0.02410  -0.1297   0.9048   0.0451
  -6.750  -0.1988   0.02698   0.02038  -0.1298   0.8973   0.0440
  -6.500  -0.1682   0.02452   0.01754  -0.1310   0.8926   0.0438
  -6.250  -0.1332   0.02264   0.01532  -0.1328   0.8892   0.0442
  -6.000  -0.1105   0.02142   0.01386  -0.1321   0.8819   0.0456
  -5.750  -0.0808   0.01986   0.01224  -0.1328   0.8773   0.0472
  -5.500  -0.0477   0.01874   0.01105  -0.1339   0.8738   0.0488
  -5.250  -0.0260   0.01809   0.01036  -0.1328   0.8669   0.0504
  -5.000   0.0022   0.01737   0.00956  -0.1330   0.8620   0.0528
  -4.750   0.0327   0.01655   0.00869  -0.1338   0.8584   0.0569
  -4.500   0.0540   0.01609   0.00827  -0.1329   0.8526   0.0620
  -4.250   0.0796   0.01548   0.00765  -0.1329   0.8479   0.0705
  -4.000   0.1082   0.01444   0.00690  -0.1337   0.8443   0.1257
  -3.750   0.1347   0.01341   0.00658  -0.1348   0.8406   0.2831
  -3.500   0.1575   0.01274   0.00650  -0.1349   0.8354   0.4296
  -3.250   0.1798   0.01243   0.00690  -0.1335   0.8314   0.5975
  -3.000   0.2055   0.01293   0.00749  -0.1321   0.8284   0.6851
  -2.750   0.2312   0.01351   0.00798  -0.1310   0.8254   0.7218
  -2.500   0.2495   0.01404   0.00851  -0.1285   0.8209   0.7396
  -2.250   0.2712   0.01447   0.00889  -0.1266   0.8172   0.7555
  -2.000   0.2946   0.01483   0.00918  -0.1250   0.8141   0.7706
  -1.750   0.3205   0.01511   0.00938  -0.1240   0.8117   0.7840
  -1.500   0.3353   0.01548   0.00976  -0.1208   0.8079   0.7936
  -1.250   0.3527   0.01577   0.01004  -0.1185   0.8039   0.8049
  -1.000   0.3758   0.01595   0.01017  -0.1173   0.8006   0.8163
  -0.750   0.3978   0.01608   0.01025  -0.1156   0.7980   0.8258
  -0.500   0.4220   0.01617   0.01030  -0.1145   0.7959   0.8352
  -0.250   0.4389   0.01647   0.01059  -0.1127   0.7916   0.8454
   0.000   0.4529   0.01661   0.01075  -0.1097   0.7875   0.8534
   0.250   0.4768   0.01668   0.01079  -0.1090   0.7844   0.8620
   0.500   0.5010   0.01668   0.01076  -0.1080   0.7819   0.8696
   0.750   0.5306   0.01670   0.01072  -0.1084   0.7799   0.8765
   1.000   0.5380   0.01703   0.01112  -0.1048   0.7742   0.8833
   1.250   0.5649   0.01716   0.01124  -0.1051   0.7705   0.8888
   1.500   0.5899   0.01709   0.01116  -0.1045   0.7675   0.8931
   1.750   0.6211   0.01704   0.01108  -0.1052   0.7652   0.8972
   2.000   0.6388   0.01740   0.01149  -0.1039   0.7600   0.9020
   2.250   0.6608   0.01751   0.01162  -0.1032   0.7554   0.9057
   2.500   0.6909   0.01741   0.01153  -0.1036   0.7520   0.9088
   2.750   0.7267   0.01726   0.01134  -0.1051   0.7493   0.9117
   3.000   0.7425   0.01761   0.01177  -0.1035   0.7424   0.9155
   3.250   0.7745   0.01748   0.01165  -0.1043   0.7376   0.9181
   3.500   0.8112   0.01716   0.01132  -0.1058   0.7341   0.9202
   3.750   0.8288   0.01732   0.01155  -0.1041   0.7266   0.9236
   4.000   0.8628   0.01699   0.01124  -0.1051   0.7208   0.9263
   4.250   0.8953   0.01678   0.01104  -0.1059   0.7146   0.9288
   4.500   0.9237   0.01660   0.01090  -0.1060   0.7065   0.9313
   4.750   0.9562   0.01623   0.01055  -0.1065   0.6998   0.9339
   5.000   0.9797   0.01603   0.01042  -0.1056   0.6908   0.9376
   5.250   1.0102   0.01579   0.01020  -0.1059   0.6832   0.9404
   5.500   1.0386   0.01554   0.01000  -0.1059   0.6740   0.9435
   5.750   1.0627   0.01534   0.00988  -0.1051   0.6639   0.9473
   6.000   1.0932   0.01497   0.00952  -0.1053   0.6541   0.9513
   6.250   1.1162   0.01474   0.00937  -0.1043   0.6419   0.9565
   6.500   1.1379   0.01455   0.00929  -0.1030   0.6281   0.9622
   6.750   1.1613   0.01435   0.00916  -0.1021   0.6119   0.9698
   7.000   1.1856   0.01422   0.00912  -0.1016   0.5911   0.9854
   7.250   1.2052   0.01419   0.00913  -0.1002   0.5634   1.0000
   7.500   1.2206   0.01432   0.00917  -0.0980   0.5209   1.0000
   7.750   1.2284   0.01487   0.00938  -0.0946   0.4623   1.0000
   8.000   1.2299   0.01598   0.01011  -0.0906   0.4033   1.0000
   8.250   1.2293   0.01733   0.01114  -0.0867   0.3504   1.0000
   8.500   1.2286   0.01881   0.01235  -0.0831   0.3031   1.0000
   8.750   1.2283   0.02041   0.01371  -0.0799   0.2615   1.0000
   9.000   1.2299   0.02205   0.01515  -0.0772   0.2247   1.0000
   9.250   1.2327   0.02374   0.01666  -0.0749   0.1947   1.0000
   9.500   1.2360   0.02549   0.01824  -0.0728   0.1713   1.0000
   9.750   1.2429   0.02709   0.01976  -0.0712   0.1512   1.0000
  10.000   1.2496   0.02875   0.02134  -0.0696   0.1356   1.0000
  10.250   1.2569   0.03041   0.02294  -0.0681   0.1233   1.0000
  10.500   1.2634   0.03217   0.02464  -0.0666   0.1133   1.0000
  10.750   1.2732   0.03372   0.02619  -0.0655   0.1042   1.0000
  11.000   1.2828   0.03533   0.02782  -0.0643   0.0969   1.0000
  11.250   1.2921   0.03696   0.02943  -0.0632   0.0907   1.0000
  11.500   1.3029   0.03857   0.03108  -0.0621   0.0853   1.0000
  11.750   1.3143   0.04007   0.03263  -0.0612   0.0802   1.0000
  12.000   1.3257   0.04180   0.03428  -0.0601   0.0756   1.0000
  12.250   1.3385   0.04324   0.03589  -0.0593   0.0720   1.0000
  12.500   1.3505   0.04478   0.03749  -0.0585   0.0684   1.0000
  12.750   1.3686   0.04635   0.03893  -0.0578   0.0643   1.0000
  13.000   1.3791   0.04797   0.04076  -0.0570   0.0621   1.0000
  13.250   1.3909   0.04963   0.04258  -0.0563   0.0594   1.0000
  13.500   1.4017   0.05134   0.04433  -0.0556   0.0568   1.0000
  13.750   1.4235   0.05305   0.04600  -0.0552   0.0534   1.0000
  14.000   1.4293   0.05510   0.04828  -0.0543   0.0519   1.0000
  14.250   1.4357   0.05723   0.05060  -0.0536   0.0498   1.0000
  14.500   1.4410   0.05938   0.05287  -0.0530   0.0477   1.0000
  14.750   1.4488   0.06141   0.05489  -0.0526   0.0457   1.0000
  15.000   1.3158   0.06855   0.06311  -0.0443   0.0466   1.0000
  15.250   1.3246   0.07129   0.06584  -0.0438   0.0441   1.0000
  15.500   1.3096   0.07543   0.07029  -0.0436   0.0433   1.0000
  15.750   1.2900   0.07954   0.07471  -0.0434   0.0424   1.0000
  16.000   1.2728   0.08357   0.07901  -0.0437   0.0414   1.0000
  16.250   1.2583   0.08759   0.08326  -0.0444   0.0403   1.0000
  16.500   1.2454   0.09158   0.08743  -0.0456   0.0390   1.0000
  16.750   1.2374   0.09510   0.09105  -0.0468   0.0379   1.0000
  17.000   1.2361   0.09767   0.09363  -0.0474   0.0361   1.0000
  17.250   1.2137   0.10335   0.09957  -0.0497   0.0358   1.0000
  17.500   1.1882   0.10977   0.10628  -0.0530   0.0355   1.0000
  17.750   1.1616   0.11672   0.11350  -0.0569   0.0354   1.0000
  18.000   1.1309   0.12475   0.12180  -0.0618   0.0354   1.0000
  18.250   1.0983   0.13359   0.13088  -0.0675   0.0356   1.0000
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