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 S807 Airfoil (s807-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NREL's S807 Airfoil (s807-nr)
Reynolds number: 1,000,000
Max Cl/Cd: 106.69 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s807-nr-1000000.txt
Download as CSV file: xf-s807-nr-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -1.0226   0.10823   0.10454  -0.0382   1.0000   0.0120
 -19.500  -1.0255   0.10468   0.10092  -0.0393   1.0000   0.0121
 -19.250  -1.0273   0.10134   0.09750  -0.0402   1.0000   0.0122
 -19.000  -1.0291   0.09805   0.09414  -0.0411   1.0000   0.0124
 -18.750  -1.0300   0.09497   0.09100  -0.0418   1.0000   0.0124
 -18.500  -1.0301   0.09191   0.08787  -0.0425   1.0000   0.0126
 -18.250  -1.0300   0.08900   0.08490  -0.0431   1.0000   0.0127
 -18.000  -1.0292   0.08614   0.08197  -0.0437   1.0000   0.0128
 -17.750  -1.0276   0.08340   0.07917  -0.0442   1.0000   0.0129
 -17.500  -1.0263   0.08082   0.07653  -0.0445   1.0000   0.0130
 -17.250  -1.0300   0.07805   0.07371  -0.0443   1.0000   0.0133
 -17.000  -1.0304   0.07539   0.07103  -0.0444   1.0000   0.0136
 -16.750  -1.0298   0.07282   0.06843  -0.0446   1.0000   0.0138
 -16.500  -1.0277   0.07051   0.06608  -0.0445   1.0000   0.0139
 -16.250  -1.0254   0.06820   0.06373  -0.0445   1.0000   0.0140
 -16.000  -1.0233   0.06591   0.06140  -0.0445   1.0000   0.0142
 -15.750  -1.0193   0.06387   0.05932  -0.0443   1.0000   0.0144
 -15.500  -1.0160   0.06176   0.05718  -0.0441   1.0000   0.0147
 -15.250  -1.0126   0.05972   0.05510  -0.0438   1.0000   0.0149
 -15.000  -1.0084   0.05780   0.05314  -0.0434   1.0000   0.0151
 -14.750  -1.0053   0.05578   0.05107  -0.0431   1.0000   0.0152
 -14.500  -1.0011   0.05394   0.04919  -0.0426   1.0000   0.0154
 -14.250  -0.9958   0.05221   0.04742  -0.0421   1.0000   0.0157
 -14.000  -0.9919   0.05037   0.04554  -0.0415   1.0000   0.0158
 -13.750  -0.9851   0.04886   0.04399  -0.0409   1.0000   0.0159
 -13.500  -0.9848   0.04684   0.04193  -0.0401   1.0000   0.0162
 -13.250  -0.9898   0.04442   0.03947  -0.0391   1.0000   0.0166
 -13.000  -0.9899   0.04249   0.03751  -0.0382   1.0000   0.0168
 -12.750  -0.9896   0.04064   0.03563  -0.0371   1.0000   0.0170
 -12.500  -0.9871   0.03906   0.03403  -0.0360   1.0000   0.0174
 -12.250  -0.9878   0.03734   0.03227  -0.0346   1.0000   0.0175
 -12.000  -0.9866   0.03585   0.03075  -0.0332   1.0000   0.0178
 -11.750  -0.9880   0.03422   0.02909  -0.0315   1.0000   0.0181
 -11.500  -0.9894   0.03268   0.02751  -0.0297   1.0000   0.0183
 -11.250  -0.9916   0.03115   0.02595  -0.0277   1.0000   0.0185
 -11.000  -0.9951   0.02965   0.02441  -0.0254   1.0000   0.0187
 -10.750  -1.0012   0.02816   0.02288  -0.0227   1.0000   0.0190
 -10.500  -1.0127   0.02663   0.02131  -0.0192   1.0000   0.0191
 -10.250  -1.0371   0.02498   0.01961  -0.0139   1.0000   0.0191
 -10.000  -1.0060   0.02352   0.01810  -0.0179   0.9971   0.0195
  -9.500  -0.9133   0.01976   0.01428  -0.0328   0.9865   0.0219
  -9.250  -0.8608   0.01848   0.01295  -0.0402   0.9834   0.0231
  -9.000  -0.8116   0.01709   0.01153  -0.0472   0.9818   0.0252
  -8.750  -0.7904   0.01613   0.01055  -0.0475   0.9765   0.0270
  -8.500  -0.7576   0.01528   0.00972  -0.0499   0.9740   0.0312
  -8.250  -0.7221   0.01426   0.00880  -0.0531   0.9722   0.0464
  -8.000  -0.6851   0.01317   0.00788  -0.0567   0.9707   0.0739
  -7.750  -0.6466   0.01212   0.00702  -0.0604   0.9696   0.1113
  -7.500  -0.6145   0.01096   0.00613  -0.0628   0.9673   0.1639
  -7.250  -0.5899   0.00972   0.00522  -0.0637   0.9629   0.2320
  -7.000  -0.5542   0.00826   0.00425  -0.0670   0.9606   0.3380
  -6.750  -0.5140   0.00781   0.00395  -0.0698   0.9586   0.3791
  -6.500  -0.4727   0.00760   0.00376  -0.0725   0.9570   0.3965
  -6.250  -0.4302   0.00743   0.00360  -0.0755   0.9558   0.4082
  -6.000  -0.4069   0.00732   0.00345  -0.0744   0.9498   0.4147
  -5.750  -0.3725   0.00713   0.00327  -0.0756   0.9450   0.4208
  -5.500  -0.3309   0.00696   0.00308  -0.0782   0.9412   0.4277
  -5.250  -0.3143   0.00687   0.00294  -0.0755   0.9274   0.4316
  -5.000  -0.2796   0.00673   0.00283  -0.0767   0.9088   0.4410
  -4.750  -0.2127   0.00686   0.00256  -0.0843   0.8162   0.4501
  -4.500  -0.1931   0.00727   0.00258  -0.0824   0.7206   0.4534
  -4.250  -0.1705   0.00756   0.00258  -0.0813   0.6514   0.4554
  -4.000  -0.1456   0.00777   0.00257  -0.0806   0.5970   0.4571
  -3.750  -0.1195   0.00795   0.00254  -0.0802   0.5520   0.4587
  -3.500  -0.0923   0.00810   0.00252  -0.0801   0.5156   0.4604
  -3.250  -0.0645   0.00821   0.00249  -0.0800   0.4861   0.4618
  -3.000  -0.0364   0.00832   0.00246  -0.0800   0.4630   0.4630
  -2.750  -0.0079   0.00841   0.00244  -0.0801   0.4437   0.4639
  -2.500   0.0205   0.00841   0.00237  -0.0802   0.4271   0.4661
  -2.000   0.0778   0.00849   0.00234  -0.0804   0.4009   0.4697
  -1.750   0.1066   0.00855   0.00235  -0.0806   0.3902   0.4712
  -1.500   0.1353   0.00862   0.00235  -0.0807   0.3799   0.4727
  -1.250   0.1643   0.00867   0.00236  -0.0808   0.3717   0.4743
  -1.000   0.1931   0.00874   0.00237  -0.0810   0.3635   0.4758
  -0.750   0.2221   0.00879   0.00239  -0.0811   0.3569   0.4773
  -0.500   0.2512   0.00885   0.00240  -0.0813   0.3508   0.4786
  -0.250   0.2799   0.00894   0.00243  -0.0814   0.3444   0.4798
   0.000   0.3089   0.00895   0.00244  -0.0815   0.3397   0.4818
   0.250   0.3379   0.00897   0.00245  -0.0817   0.3351   0.4840
   0.500   0.3666   0.00903   0.00250  -0.0818   0.3302   0.4858
   0.750   0.3951   0.00912   0.00256  -0.0819   0.3250   0.4875
   1.000   0.4243   0.00916   0.00260  -0.0820   0.3218   0.4892
   1.250   0.4532   0.00922   0.00265  -0.0822   0.3179   0.4909
   1.500   0.4818   0.00930   0.00271  -0.0822   0.3140   0.4926
   1.750   0.5100   0.00942   0.00279  -0.0822   0.3095   0.4942
   2.000   0.5389   0.00949   0.00286  -0.0824   0.3071   0.4956
   2.250   0.5679   0.00956   0.00292  -0.0825   0.3046   0.4968
   2.500   0.5966   0.00957   0.00297  -0.0826   0.3018   0.4995
   2.750   0.6251   0.00964   0.00305  -0.0827   0.2988   0.5018
   3.000   0.6533   0.00975   0.00315  -0.0827   0.2956   0.5039
   3.250   0.6811   0.00991   0.00329  -0.0826   0.2919   0.5059
   3.500   0.7099   0.00996   0.00337  -0.0827   0.2902   0.5079
   3.750   0.7386   0.01003   0.00346  -0.0828   0.2882   0.5098
   4.000   0.7670   0.01012   0.00356  -0.0828   0.2860   0.5115
   4.250   0.7952   0.01022   0.00367  -0.0828   0.2837   0.5130
   4.500   0.8233   0.01032   0.00377  -0.0828   0.2812   0.5152
   4.750   0.8509   0.01045   0.00391  -0.0827   0.2781   0.5178
   5.000   0.8784   0.01061   0.00409  -0.0826   0.2754   0.5201
   5.250   0.9068   0.01068   0.00421  -0.0827   0.2739   0.5224
   5.500   0.9351   0.01074   0.00431  -0.0827   0.2714   0.5248
   5.750   0.9633   0.01083   0.00441  -0.0827   0.2684   0.5271
   6.000   0.9909   0.01095   0.00454  -0.0826   0.2654   0.5291
   6.250   1.0178   0.01114   0.00471  -0.0824   0.2620   0.5307
   6.500   1.0451   0.01126   0.00488  -0.0823   0.2591   0.5339
   6.750   1.0734   0.01131   0.00498  -0.0823   0.2567   0.5366
   7.000   1.1013   0.01138   0.00511  -0.0823   0.2538   0.5392
   7.250   1.1286   0.01150   0.00525  -0.0821   0.2506   0.5417
   7.500   1.1552   0.01168   0.00542  -0.0819   0.2468   0.5442
   7.750   1.1818   0.01185   0.00561  -0.0816   0.2432   0.5465
   8.000   1.2097   0.01191   0.00573  -0.0816   0.2399   0.5492
   8.250   1.2369   0.01201   0.00587  -0.0815   0.2354   0.5528
   8.500   1.2629   0.01219   0.00606  -0.0812   0.2308   0.5560
   8.750   1.2895   0.01235   0.00626  -0.0809   0.2272   0.5590
   9.000   1.3163   0.01247   0.00643  -0.0807   0.2227   0.5620
   9.250   1.3420   0.01267   0.00662  -0.0803   0.2168   0.5646
   9.500   1.3678   0.01285   0.00684  -0.0800   0.2112   0.5681
   9.750   1.3933   0.01306   0.00706  -0.0796   0.2031   0.5718
  10.000   1.4179   0.01332   0.00733  -0.0791   0.1937   0.5755
  10.250   1.4410   0.01368   0.00765  -0.0784   0.1804   0.5792
  10.500   1.4616   0.01424   0.00810  -0.0773   0.1612   0.5825
  10.750   1.4798   0.01494   0.00870  -0.0759   0.1406   0.5870
  11.000   1.4973   0.01564   0.00933  -0.0744   0.1234   0.5912
  11.250   1.5139   0.01635   0.00997  -0.0727   0.1090   0.5955
  11.500   1.5287   0.01702   0.01059  -0.0707   0.0971   0.5994
  11.750   1.5423   0.01766   0.01122  -0.0685   0.0870   0.6042
  12.000   1.5552   0.01836   0.01190  -0.0662   0.0778   0.6093
  12.250   1.5666   0.01911   0.01263  -0.0638   0.0696   0.6145
  12.500   1.5791   0.01981   0.01333  -0.0616   0.0637   0.6201
  12.750   1.5910   0.02052   0.01408  -0.0594   0.0584   0.6267
  13.000   1.6011   0.02135   0.01491  -0.0570   0.0538   0.6332
  13.250   1.6121   0.02211   0.01574  -0.0548   0.0501   0.6404
  13.500   1.6205   0.02303   0.01670  -0.0524   0.0465   0.6482
  13.750   1.6290   0.02398   0.01770  -0.0502   0.0436   0.6563
  14.000   1.6367   0.02499   0.01877  -0.0480   0.0411   0.6657
  14.250   1.6406   0.02627   0.02011  -0.0456   0.0386   0.6753
  14.500   1.6464   0.02749   0.02142  -0.0436   0.0369   0.6868
  14.750   1.6503   0.02892   0.02295  -0.0418   0.0352   0.7000
  15.000   1.6502   0.03073   0.02486  -0.0399   0.0336   0.7147
  15.250   1.6472   0.03295   0.02719  -0.0384   0.0320   0.7311
  15.500   1.6480   0.03507   0.02945  -0.0375   0.0311   0.7515
  15.750   1.6450   0.03776   0.03231  -0.0370   0.0301   0.7766
  16.000   1.6384   0.04111   0.03585  -0.0370   0.0292   0.8131
  16.250   1.6219   0.04485   0.03997  -0.0364   0.0285   1.0000
  16.500   1.6071   0.05005   0.04529  -0.0380   0.0277   1.0000
  16.750   1.5877   0.05624   0.05161  -0.0403   0.0271   1.0000
  17.000   1.5690   0.06249   0.05801  -0.0428   0.0267   1.0000
  17.250   1.5482   0.06913   0.06479  -0.0454   0.0265   1.0000
  17.500   1.5256   0.07609   0.07189  -0.0483   0.0263   1.0000
  17.750   1.5041   0.08301   0.07893  -0.0513   0.0259   1.0000
<< Back to NREL's S807 Airfoil (s807-nr)

Polar data table (+)

Polar graphs


<< Back to NREL's S807 Airfoil (s807-nr)