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 S819 Airfoil (s819-nr) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NREL's S819 Airfoil (s819-nr)
Reynolds number: 500,000
Max Cl/Cd: 77.59 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s819-nr-500000.txt
Download as CSV file: xf-s819-nr-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S819 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
  ------ -------- --------- --------- -------- -------- --------
 -19.000  -0.6401   0.16163   0.15889  -0.0253   1.0000   0.0108
 -18.750  -0.6577   0.15345   0.15062  -0.0295   1.0000   0.0107
 -18.500  -0.6764   0.14565   0.14271  -0.0335   1.0000   0.0106
 -18.250  -0.6924   0.13894   0.13590  -0.0369   1.0000   0.0106
 -18.000  -0.7088   0.13248   0.12934  -0.0400   1.0000   0.0106
 -17.750  -0.7251   0.12636   0.12310  -0.0429   1.0000   0.0106
 -17.500  -0.7401   0.12070   0.11733  -0.0455   1.0000   0.0106
 -17.250  -0.7560   0.11522   0.11173  -0.0479   1.0000   0.0105
 -17.000  -0.7684   0.11040   0.10682  -0.0498   1.0000   0.0106
 -16.750  -0.7810   0.10573   0.10204  -0.0516   1.0000   0.0106
 -16.500  -0.7932   0.10123   0.09743  -0.0532   1.0000   0.0106
 -16.250  -0.8042   0.09706   0.09315  -0.0546   1.0000   0.0106
 -16.000  -0.8134   0.09315   0.08914  -0.0557   1.0000   0.0107
 -15.750  -0.8222   0.08942   0.08531  -0.0567   1.0000   0.0107
 -15.500  -0.8297   0.08589   0.08169  -0.0574   1.0000   0.0108
 -15.250  -0.8364   0.08259   0.07829  -0.0580   1.0000   0.0108
 -15.000  -0.8416   0.07952   0.07510  -0.0584   1.0000   0.0108
 -14.750  -0.8457   0.07657   0.07206  -0.0586   1.0000   0.0110
 -14.500  -0.8487   0.07377   0.06918  -0.0586   1.0000   0.0111
 -14.250  -0.8496   0.07118   0.06649  -0.0585   1.0000   0.0112
 -14.000  -0.8497   0.06865   0.06386  -0.0582   1.0000   0.0114
 -13.750  -0.8474   0.06640   0.06153  -0.0578   1.0000   0.0115
 -13.500  -0.8438   0.06426   0.05931  -0.0573   1.0000   0.0116
 -13.250  -0.8404   0.06218   0.05713  -0.0566   1.0000   0.0120
 -13.000  -0.8359   0.06031   0.05516  -0.0559   1.0000   0.0121
 -12.750  -0.8391   0.05849   0.05321  -0.0551   1.0000   0.0125
 -12.500  -0.8389   0.05686   0.05148  -0.0542   1.0000   0.0127
 -12.250  -0.8549   0.05523   0.04969  -0.0531   1.0000   0.0129
 -12.000  -0.8661   0.05374   0.04808  -0.0516   1.0000   0.0130
 -11.750  -0.8818   0.05246   0.04666  -0.0495   1.0000   0.0130
 -11.500  -0.7557   0.05167   0.04609  -0.0491   1.0000   0.0139
 -11.250  -0.7204   0.05165   0.04615  -0.0473   1.0000   0.0145
 -11.000  -0.7003   0.05111   0.04561  -0.0457   1.0000   0.0150
 -10.750  -0.6863   0.05029   0.04476  -0.0444   1.0000   0.0158
 -10.500  -0.6840   0.04881   0.04319  -0.0434   1.0000   0.0164
 -10.250  -0.6959   0.04670   0.04093  -0.0427   1.0000   0.0167
 -10.000  -0.7127   0.04473   0.03883  -0.0416   1.0000   0.0170
  -9.250  -0.5792   0.04910   0.04362  -0.0323   1.0000   0.0231
  -9.000  -0.5577   0.05019   0.04486  -0.0292   1.0000   0.0244
  -8.750  -0.5531   0.04901   0.04367  -0.0276   1.0000   0.0265
  -8.500  -0.5547   0.04703   0.04163  -0.0267   1.0000   0.0273
  -8.250  -0.5372   0.04897   0.04383  -0.0220   1.0000   0.0320
  -6.500  -0.4021   0.03250   0.02714  -0.0447   0.9734   0.0274
  -6.250  -0.3977   0.02798   0.02246  -0.0491   0.9631   0.0205
  -6.000  -0.3725   0.02441   0.01873  -0.0554   0.9578   0.0162
  -5.750  -0.3825   0.02051   0.01466  -0.0564   0.9339   0.0157
  -5.500  -0.3691   0.01771   0.01163  -0.0598   0.9141   0.0143
  -5.250  -0.3420   0.01673   0.01052  -0.0612   0.8965   0.0134
  -5.000  -0.3168   0.01553   0.00914  -0.0627   0.8742   0.0134
  -4.750  -0.2933   0.01451   0.00790  -0.0633   0.8509   0.0137
  -4.500  -0.2704   0.01392   0.00711  -0.0633   0.8276   0.0141
  -4.250  -0.2465   0.01354   0.00654  -0.0631   0.8066   0.0154
  -3.750  -0.1971   0.01305   0.00573  -0.0627   0.7691   0.0200
  -3.500  -0.1717   0.01289   0.00543  -0.0625   0.7520   0.0243
  -3.250  -0.1591   0.01053   0.00389  -0.0627   0.7361   0.3004
  -3.000  -0.1310   0.01072   0.00407  -0.0630   0.7211   0.3226
  -2.500  -0.0753   0.01103   0.00429  -0.0633   0.6924   0.3379
  -2.250  -0.0480   0.01097   0.00419  -0.0634   0.6791   0.3394
  -2.000  -0.0204   0.01094   0.00411  -0.0635   0.6666   0.3408
  -1.750   0.0071   0.01092   0.00404  -0.0636   0.6543   0.3422
  -1.250   0.0624   0.01089   0.00390  -0.0638   0.6295   0.3452
  -1.000   0.0902   0.01088   0.00384  -0.0640   0.6181   0.3467
  -0.750   0.1179   0.01089   0.00379  -0.0641   0.6073   0.3482
  -0.500   0.1459   0.01090   0.00375  -0.0642   0.5960   0.3495
  -0.250   0.1734   0.01082   0.00366  -0.0644   0.5851   0.3518
   0.000   0.2009   0.01079   0.00363  -0.0645   0.5744   0.3539
   0.250   0.2287   0.01079   0.00362  -0.0646   0.5636   0.3561
   0.500   0.2566   0.01080   0.00362  -0.0648   0.5536   0.3583
   0.750   0.2842   0.01085   0.00362  -0.0649   0.5440   0.3607
   1.000   0.3124   0.01087   0.00363  -0.0651   0.5339   0.3631
   1.250   0.3402   0.01091   0.00364  -0.0652   0.5243   0.3654
   1.500   0.3676   0.01089   0.00365  -0.0653   0.5145   0.3686
   1.750   0.3956   0.01090   0.00369  -0.0655   0.5050   0.3717
   2.000   0.4229   0.01099   0.00375  -0.0656   0.4963   0.3748
   2.250   0.4511   0.01103   0.00380  -0.0657   0.4872   0.3781
   2.500   0.4786   0.01110   0.00385  -0.0658   0.4790   0.3815
   2.750   0.5064   0.01110   0.00392  -0.0660   0.4700   0.3854
   3.000   0.5338   0.01119   0.00402  -0.0660   0.4618   0.3895
   3.250   0.5615   0.01127   0.00411  -0.0661   0.4534   0.3936
   3.500   0.5889   0.01136   0.00421  -0.0662   0.4460   0.3978
   3.750   0.6165   0.01141   0.00432  -0.0663   0.4381   0.4022
   4.000   0.6436   0.01154   0.00445  -0.0663   0.4308   0.4067
   4.250   0.6711   0.01163   0.00456  -0.0664   0.4225   0.4109
   4.500   0.6978   0.01172   0.00469  -0.0663   0.4143   0.4157
   4.750   0.7249   0.01180   0.00483  -0.0663   0.4058   0.4206
   5.000   0.7515   0.01195   0.00497  -0.0662   0.3978   0.4254
   5.250   0.7783   0.01203   0.00511  -0.0662   0.3896   0.4303
   5.500   0.8048   0.01216   0.00529  -0.0661   0.3823   0.4355
   5.750   0.8314   0.01229   0.00545  -0.0660   0.3745   0.4408
   6.000   0.8574   0.01242   0.00563  -0.0658   0.3668   0.4459
   6.250   0.8836   0.01254   0.00582  -0.0656   0.3586   0.4516
   6.500   0.9093   0.01272   0.00601  -0.0653   0.3514   0.4572
   6.750   0.9353   0.01283   0.00621  -0.0652   0.3435   0.4629
   7.000   0.9604   0.01301   0.00644  -0.0648   0.3359   0.4693
   7.250   0.9856   0.01316   0.00665  -0.0645   0.3272   0.4756
   7.500   1.0104   0.01333   0.00690  -0.0641   0.3190   0.4822
   7.750   1.0343   0.01355   0.00714  -0.0635   0.3096   0.4891
   8.000   1.0585   0.01372   0.00740  -0.0630   0.2990   0.4958
   8.250   1.0814   0.01396   0.00768  -0.0623   0.2874   0.5029
   8.500   1.1033   0.01422   0.00798  -0.0615   0.2734   0.5097
   8.750   1.1240   0.01453   0.00831  -0.0604   0.2557   0.5171
   9.000   1.1397   0.01499   0.00869  -0.0586   0.2316   0.5240
   9.250   1.1513   0.01560   0.00920  -0.0562   0.2011   0.5311
   9.750   1.1709   0.01722   0.01063  -0.0511   0.1511   0.5455
  10.250   1.1906   0.01889   0.01222  -0.0464   0.1170   0.5616
  10.500   1.2002   0.01976   0.01307  -0.0442   0.1042   0.5703
  11.000   1.2190   0.02154   0.01491  -0.0400   0.0842   0.5885
  11.250   1.2274   0.02253   0.01595  -0.0380   0.0763   0.5987
  11.500   1.2331   0.02373   0.01717  -0.0360   0.0691   0.6087
  11.750   1.2418   0.02480   0.01832  -0.0344   0.0633   0.6202
  12.000   1.2446   0.02632   0.01989  -0.0325   0.0574   0.6314
  12.250   1.2531   0.02754   0.02123  -0.0312   0.0529   0.6434
  12.500   1.2540   0.02940   0.02313  -0.0297   0.0480   0.6554
  12.750   1.2610   0.03092   0.02476  -0.0288   0.0442   0.6686
  13.000   1.2620   0.03300   0.02691  -0.0279   0.0403   0.6820
  13.250   1.2646   0.03507   0.02911  -0.0272   0.0371   0.6967
  13.500   1.2664   0.03729   0.03144  -0.0267   0.0341   0.7128
  13.750   1.2611   0.04033   0.03457  -0.0263   0.0315   0.7294
  14.000   1.2651   0.04255   0.03697  -0.0262   0.0293   0.7503
  14.250   1.2642   0.04532   0.03984  -0.0262   0.0266   0.7743
  14.500   1.2590   0.04861   0.04331  -0.0263   0.0248   0.8043
  14.750   1.2531   0.05164   0.04663  -0.0259   0.0241   0.8613
  15.000   1.2492   0.05437   0.04958  -0.0256   0.0226   1.0000
  15.250   1.2453   0.05807   0.05333  -0.0266   0.0212   1.0000
  15.500   1.2374   0.06243   0.05774  -0.0278   0.0198   1.0000
  15.750   1.2380   0.06576   0.06117  -0.0289   0.0188   1.0000
  16.000   1.2361   0.06952   0.06500  -0.0302   0.0176   1.0000
  16.250   1.2302   0.07393   0.06947  -0.0317   0.0167   1.0000
  16.500   1.2209   0.07891   0.07451  -0.0336   0.0158   1.0000
  16.750   1.2222   0.08247   0.07816  -0.0350   0.0148   1.0000
  17.000   1.2186   0.08683   0.08261  -0.0368   0.0141   1.0000
  17.250   1.2148   0.09126   0.08711  -0.0387   0.0133   1.0000
  17.500   1.2069   0.09643   0.09235  -0.0410   0.0128   1.0000
  17.750   1.1996   0.10158   0.09759  -0.0433   0.0122   1.0000
<< Back to NREL's S819 Airfoil (s819-nr)

Polar data table (+)

Polar graphs


<< Back to NREL's S819 Airfoil (s819-nr)