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FX S 02-196 AIRFOIL (fxs02196-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX S 02-196 AIRFOIL (fxs02196-il)
Reynolds number: 50,000
Max Cl/Cd: 4.7 at α=11.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fxs02196-il-50000.txt
Download as CSV file: xf-fxs02196-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX S 02-196 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2105   0.12645   0.12073  -0.0532   0.9632   0.3300
 -10.250  -0.3114   0.10690   0.10128  -0.0715   0.9595   0.1728
 -10.000  -0.3647   0.09538   0.08983  -0.0790   0.9512   0.1517
  -9.750  -0.4534   0.08377   0.07819  -0.0877   0.9429   0.1419
  -9.500  -0.4873   0.08004   0.07442  -0.0881   0.9341   0.1391
  -9.250  -0.5376   0.07700   0.07125  -0.0868   0.9250   0.1367
  -9.000  -0.5925   0.07327   0.06704  -0.0855   0.9177   0.1325
  -8.750  -0.6047   0.07113   0.06481  -0.0827   0.9109   0.1314
  -8.500  -0.6083   0.06795   0.06137  -0.0820   0.9051   0.1294
  -8.250  -0.6067   0.06416   0.05708  -0.0826   0.9004   0.1265
  -8.000  -0.6182   0.06173   0.05413  -0.0801   0.8958   0.1243
  -7.750  -0.6237   0.05987   0.05173  -0.0775   0.8922   0.1227
  -7.500  -0.6156   0.05797   0.04957  -0.0761   0.8895   0.1221
  -7.250  -0.6042   0.05620   0.04750  -0.0750   0.8873   0.1219
  -7.000  -0.5904   0.05468   0.04566  -0.0740   0.8856   0.1220
  -6.750  -0.5744   0.05336   0.04405  -0.0733   0.8839   0.1233
  -6.500  -0.5511   0.05223   0.04292  -0.0732   0.8815   0.1261
  -6.250  -0.5171   0.05132   0.04181  -0.0743   0.8783   0.1293
  -6.000  -0.5075   0.05079   0.04114  -0.0719   0.8771   0.1310
  -5.750  -0.7197   0.05018   0.04100  -0.0386   1.0000   0.1215
  -5.500  -0.7009   0.04883   0.03933  -0.0381   1.0000   0.1231
  -5.250  -0.6832   0.04771   0.03826  -0.0371   1.0000   0.1256
  -5.000  -0.6649   0.04684   0.03731  -0.0361   1.0000   0.1282
  -4.750  -0.6464   0.04616   0.03652  -0.0347   1.0000   0.1305
  -4.500  -0.6280   0.04568   0.03590  -0.0332   1.0000   0.1332
  -4.250  -0.6120   0.04524   0.03562  -0.0313   1.0000   0.1370
  -4.000  -0.5953   0.04494   0.03527  -0.0296   1.0000   0.1422
  -3.750  -0.5794   0.04450   0.03492  -0.0281   1.0000   0.1488
  -3.500  -0.5621   0.04390   0.03442  -0.0273   1.0000   0.1591
  -3.250  -0.5419   0.04303   0.03377  -0.0279   1.0000   0.1781
  -3.000  -0.5243   0.04100   0.03432  -0.0282   1.0000   0.3915
  -2.750  -0.5181   0.04435   0.03754  -0.0208   1.0000   0.5749
  -2.500  -0.5174   0.04653   0.03970  -0.0130   1.0000   0.6127
  -2.250  -0.5143   0.04809   0.04121  -0.0064   1.0000   0.6430
  -2.000  -0.5123   0.04931   0.04238   0.0002   1.0000   0.6671
  -1.750  -0.5077   0.05017   0.04317   0.0056   1.0000   0.6891
  -1.500  -0.5007   0.05076   0.04364   0.0099   1.0000   0.7084
  -1.250  -0.4893   0.05114   0.04385   0.0124   1.0000   0.7250
  -1.000  -0.4733   0.05199   0.04456   0.0142   0.9969   0.7437
  -0.750  -0.4549   0.05352   0.04594   0.0162   0.9913   0.7644
  -0.500  -0.4421   0.05403   0.04636   0.0190   0.9841   0.7828
  -0.250  -0.4232   0.05543   0.04764   0.0208   0.9776   0.8013
   0.000  -0.4118   0.05543   0.04754   0.0233   0.9704   0.8155
   0.250  -0.3878   0.05648   0.04844   0.0228   0.9619   0.8303
   0.500  -0.3714   0.05706   0.04890   0.0237   0.9561   0.8452
   0.750  -0.3532   0.05730   0.04905   0.0246   0.9458   0.8575
   1.000  -0.3244   0.05943   0.05103   0.0230   0.9401   0.8716
   1.250  -0.3135   0.05829   0.04982   0.0242   0.9301   0.8792
   1.500  -0.2823   0.05971   0.05109   0.0211   0.9224   0.8870
   1.750  -0.2596   0.06053   0.05181   0.0197   0.9173   0.8919
   2.000  -0.2391   0.06046   0.05166   0.0188   0.9070   0.8974
   2.250  -0.2048   0.06244   0.05352   0.0151   0.9009   0.9039
   2.500  -0.1878   0.06259   0.05360   0.0143   0.8948   0.9088
   2.750  -0.1617   0.06325   0.05419   0.0122   0.8845   0.9142
   3.000  -0.1217   0.06627   0.05713   0.0075   0.8789   0.9214
   3.250  -0.1125   0.06520   0.05603   0.0080   0.8686   0.9270
   3.500  -0.0752   0.06724   0.05802   0.0038   0.8604   0.9337
   3.750  -0.0508   0.06850   0.05924   0.0014   0.8537   0.9409
   4.000  -0.0205   0.06950   0.06023  -0.0018   0.8416   0.9484
   4.250   0.0309   0.07380   0.06450  -0.0089   0.8363   0.9589
   4.500   0.0392   0.07245   0.06318  -0.0090   0.8249   0.9669
   4.750   0.0852   0.07539   0.06612  -0.0154   0.8174   0.9826
   5.000   0.0961   0.07553   0.06626  -0.0161   0.8085   1.0000
   5.250   0.1263   0.07737   0.06806  -0.0198   0.7988   1.0000
   5.500   0.1747   0.08228   0.07292  -0.0266   0.7943   1.0000
   5.750   0.1725   0.08057   0.07122  -0.0255   0.7821   1.0000
   6.000   0.2144   0.08411   0.07473  -0.0312   0.7756   1.0000
   6.250   0.2263   0.08493   0.07556  -0.0325   0.7665   1.0000
   6.500   0.2639   0.08783   0.07844  -0.0372   0.7561   1.0000
   6.750   0.2818   0.08958   0.08019  -0.0394   0.7470   1.0000
   7.000   0.3138   0.09212   0.08273  -0.0434   0.7364   1.0000
   7.500   0.3550   0.09638   0.08699  -0.0483   0.7192   1.0000
   7.750   0.3957   0.10067   0.09127  -0.0532   0.7130   1.0000
   8.000   0.3972   0.10134   0.09197  -0.0532   0.7034   1.0000
   8.250   0.4307   0.10465   0.09527  -0.0566   0.6938   1.0000
   8.500   0.4388   0.10631   0.09695  -0.0573   0.6839   1.0000
   8.750   0.4697   0.10945   0.10010  -0.0600   0.6732   1.0000
   9.000   0.4772   0.11142   0.10210  -0.0606   0.6645   1.0000
   9.250   0.5021   0.11411   0.10482  -0.0625   0.6531   1.0000
   9.500   0.5184   0.11733   0.10807  -0.0640   0.6467   1.0000
   9.750   0.5308   0.11887   0.10965  -0.0647   0.6337   1.0000
  10.000   0.5584   0.12338   0.11421  -0.0671   0.6276   1.0000
  10.250   0.5608   0.12394   0.11483  -0.0669   0.6134   1.0000
  10.500   0.5776   0.12728   0.11822  -0.0683   0.6051   1.0000
  10.750   0.5984   0.12961   0.12063  -0.0694   0.5903   1.0000
  11.000   0.6005   0.13181   0.12289  -0.0699   0.5812   1.0000
  11.250   0.6405   0.13628   0.12746  -0.0721   0.5677   1.0000
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