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NREL's S807 Airfoil (s807-nr) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NREL's S807 Airfoil (s807-nr)
Reynolds number: 50,000
Max Cl/Cd: 21.98 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s807-nr-50000-n5.txt
Download as CSV file: xf-s807-nr-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S807 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.750  -0.6082   0.13607   0.12796  -0.0304   1.0000   0.0598
 -15.500  -0.6516   0.12135   0.11313  -0.0378   1.0000   0.0592
 -15.250  -0.6897   0.10973   0.10128  -0.0435   1.0000   0.0588
 -15.000  -0.7130   0.10189   0.09322  -0.0469   1.0000   0.0589
 -14.750  -0.7284   0.09585   0.08695  -0.0492   1.0000   0.0595
 -14.500  -0.7393   0.09076   0.08163  -0.0507   1.0000   0.0605
 -14.250  -0.7455   0.08643   0.07706  -0.0516   1.0000   0.0615
 -14.000  -0.7475   0.08274   0.07307  -0.0520   1.0000   0.0627
 -13.750  -0.7325   0.08153   0.07193  -0.0508   1.0000   0.0647
 -13.500  -0.7236   0.07967   0.07003  -0.0501   1.0000   0.0671
 -13.250  -0.7172   0.07744   0.06766  -0.0496   1.0000   0.0702
 -13.000  -0.7095   0.07538   0.06544  -0.0489   1.0000   0.0736
 -12.750  -0.6988   0.07407   0.06423  -0.0479   1.0000   0.0773
 -12.500  -0.6897   0.07244   0.06253  -0.0469   1.0000   0.0818
 -12.250  -0.6811   0.07088   0.06098  -0.0458   1.0000   0.0869
 -12.000  -0.6751   0.06911   0.05926  -0.0449   1.0000   0.0934
 -11.750  -0.6706   0.06725   0.05748  -0.0440   1.0000   0.1012
 -11.500  -0.6672   0.06529   0.05559  -0.0430   1.0000   0.1112
 -11.250  -0.6664   0.06321   0.05366  -0.0421   1.0000   0.1229
 -11.000  -0.6677   0.06103   0.05169  -0.0411   1.0000   0.1374
 -10.750  -0.6708   0.05884   0.04978  -0.0400   1.0000   0.1553
 -10.500  -0.6747   0.05688   0.04818  -0.0385   1.0000   0.1795
 -10.250  -0.6743   0.05575   0.04750  -0.0365   1.0000   0.2150
 -10.000  -0.6514   0.05775   0.04992  -0.0333   1.0000   0.2630
  -9.750  -0.6333   0.05903   0.05120  -0.0308   1.0000   0.2942
  -9.500  -0.6143   0.06043   0.05249  -0.0283   1.0000   0.3152
  -9.250  -0.6067   0.06043   0.05239  -0.0263   1.0000   0.3349
  -9.000  -0.6111   0.05925   0.05117  -0.0243   1.0000   0.3539
  -8.750  -0.6055   0.05926   0.05109  -0.0219   1.0000   0.3703
  -8.250  -0.5775   0.06054   0.05217  -0.0168   1.0000   0.3977
  -8.000  -0.5581   0.06124   0.05276  -0.0145   1.0000   0.4088
  -7.750  -0.5540   0.06079   0.05225  -0.0120   1.0000   0.4207
  -7.500  -0.5634   0.05964   0.05109  -0.0089   1.0000   0.4333
  -7.250  -0.5335   0.06036   0.05168  -0.0072   1.0000   0.4409
  -7.000  -0.5380   0.05938   0.05069  -0.0042   1.0000   0.4512
  -6.750  -0.5319   0.05885   0.05011  -0.0015   1.0000   0.4600
  -6.500  -0.5273   0.05814   0.04935   0.0011   1.0000   0.4680
  -6.000  -0.5199   0.05628   0.04743   0.0057   1.0000   0.4838
  -5.750  -0.5084   0.05566   0.04676   0.0077   1.0000   0.4903
  -5.500  -0.5165   0.05394   0.04504   0.0100   1.0000   0.4990
  -5.250  -0.4995   0.05360   0.04465   0.0119   1.0000   0.5036
  -5.000  -0.5157   0.05114   0.04218   0.0134   1.0000   0.5140
  -4.750  -0.4974   0.05097   0.04198   0.0155   1.0000   0.5171
  -4.500  -0.4863   0.05037   0.04136   0.0174   1.0000   0.5218
  -4.250  -0.4961   0.04787   0.03882   0.0177   1.0000   0.5311
  -4.000  -0.4461   0.04782   0.03865   0.0141   0.9891   0.5339
  -3.750  -0.3971   0.04726   0.03798   0.0096   0.9752   0.5378
  -3.500  -0.3555   0.04593   0.03651   0.0046   0.9582   0.5436
  -3.250  -0.3210   0.04414   0.03461   0.0000   0.9386   0.5493
  -3.000  -0.2858   0.04344   0.03388  -0.0013   0.9163   0.5520
  -2.750  -0.2523   0.04248   0.03285  -0.0030   0.8916   0.5554
  -2.500  -0.2193   0.04110   0.03141  -0.0054   0.8652   0.5597
  -2.250  -0.1902   0.03910   0.02928  -0.0090   0.8354   0.5656
  -2.000  -0.1490   0.03834   0.02845  -0.0108   0.8058   0.5678
  -1.750  -0.0991   0.03745   0.02742  -0.0144   0.7727   0.5702
  -1.500  -0.0423   0.03656   0.02627  -0.0197   0.7336   0.5732
  -1.250   0.0057   0.03572   0.02509  -0.0240   0.6920   0.5771
  -1.000   0.0390   0.03470   0.02371  -0.0273   0.6551   0.5819
  -0.750   0.0688   0.03431   0.02306  -0.0282   0.6243   0.5842
  -0.500   0.0955   0.03411   0.02267  -0.0282   0.5984   0.5863
  -0.250   0.1212   0.03391   0.02229  -0.0283   0.5768   0.5891
   0.000   0.1474   0.03365   0.02186  -0.0288   0.5584   0.5924
   0.250   0.1745   0.03325   0.02130  -0.0301   0.5425   0.5962
   0.500   0.2037   0.03270   0.02057  -0.0324   0.5284   0.6001
   0.750   0.2312   0.03266   0.02042  -0.0325   0.5161   0.6020
   1.000   0.2575   0.03261   0.02035  -0.0326   0.5039   0.6045
   1.250   0.2856   0.03255   0.02024  -0.0331   0.4937   0.6076
   1.500   0.3150   0.03244   0.02006  -0.0343   0.4843   0.6111
   1.750   0.3456   0.03226   0.01983  -0.0361   0.4753   0.6151
   2.000   0.3762   0.03215   0.01967  -0.0376   0.4671   0.6181
   2.250   0.4030   0.03224   0.01978  -0.0377   0.4594   0.6204
   2.500   0.4299   0.03234   0.01991  -0.0379   0.4520   0.6234
   2.750   0.4600   0.03244   0.01995  -0.0388   0.4463   0.6269
   3.000   0.4875   0.03255   0.02016  -0.0398   0.4395   0.6310
   3.250   0.5178   0.03264   0.02025  -0.0412   0.4335   0.6349
   3.500   0.5454   0.03286   0.02045  -0.0413   0.4285   0.6375
   3.750   0.5688   0.03316   0.02092  -0.0411   0.4223   0.6404
   4.000   0.5951   0.03343   0.02126  -0.0414   0.4170   0.6440
   4.250   0.6253   0.03371   0.02152  -0.0426   0.4128   0.6484
   4.500   0.6515   0.03413   0.02206  -0.0432   0.4081   0.6525
   4.750   0.6735   0.03461   0.02272  -0.0426   0.4030   0.6557
   5.000   0.6992   0.03502   0.02322  -0.0427   0.3984   0.6593
   5.250   0.7290   0.03540   0.02358  -0.0435   0.3946   0.6635
   5.500   0.7529   0.03612   0.02450  -0.0442   0.3898   0.6682
   5.750   0.7728   0.03682   0.02543  -0.0434   0.3856   0.6715
   6.000   0.7962   0.03743   0.02616  -0.0431   0.3815   0.6756
   6.250   0.8248   0.03793   0.02669  -0.0437   0.3779   0.6806
   6.500   0.8457   0.03891   0.02789  -0.0438   0.3733   0.6856
   6.750   0.8610   0.03992   0.02917  -0.0426   0.3688   0.6892
   7.000   0.8818   0.04076   0.03016  -0.0422   0.3648   0.6936
   7.250   0.9095   0.04138   0.03083  -0.0427   0.3611   0.6991
   7.500   0.9254   0.04260   0.03229  -0.0420   0.3567   0.7040
   7.750   0.9333   0.04410   0.03409  -0.0403   0.3517   0.7085
   8.000   0.9519   0.04514   0.03529  -0.0398   0.3473   0.7142
   8.250   0.9817   0.04562   0.03583  -0.0404   0.3435   0.7203
   8.500   0.9795   0.04773   0.03828  -0.0379   0.3382   0.7248
   8.750   0.9814   0.04970   0.04050  -0.0362   0.3328   0.7303
   9.000   1.0062   0.05032   0.04122  -0.0362   0.3282   0.7372
   9.250   1.0190   0.05150   0.04257  -0.0350   0.3237   0.7434
   9.500   0.9762   0.05609   0.04749  -0.0308   0.3171   0.7477
   9.750   0.9942   0.05688   0.04840  -0.0301   0.3122   0.7552
  10.000   1.0321   0.05646   0.04808  -0.0303   0.3080   0.7641
  10.250   0.8842   0.07187   0.06370  -0.0290   0.2967   0.7617
  10.500   0.9336   0.06905   0.06103  -0.0271   0.2939   0.7728
  11.000   0.8780   0.08274   0.07493  -0.0321   0.2767   0.7831
  11.500   0.8568   0.09249   0.08489  -0.0356   0.2605   0.7972
  12.000   0.8455   0.10076   0.09340  -0.0383   0.2450   0.8155
  12.250   0.8150   0.10900   0.10169  -0.0423   0.2342   0.8203
  12.500   0.8365   0.10844   0.10133  -0.0405   0.2300   0.8403
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