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FX 66-S-196 V1 AIRFOIL (fx66196v-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 66-S-196 V1 AIRFOIL (fx66196v-il)
Reynolds number: 100,000
Max Cl/Cd: 26.3 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx66196v-il-100000-n5.txt
Download as CSV file: xf-fx66196v-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 66-S-196 V1 AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.2910   0.09557   0.09066  -0.0909   0.8979   0.0282
 -13.000  -0.3207   0.08329   0.07826  -0.0998   0.8865   0.0277
 -12.750  -0.3491   0.07391   0.06864  -0.1073   0.8721   0.0273
 -12.500  -0.3741   0.06683   0.06127  -0.1125   0.8571   0.0271
 -12.250  -0.3941   0.06143   0.05559  -0.1158   0.8418   0.0270
 -12.000  -0.4109   0.05701   0.05088  -0.1178   0.8276   0.0270
 -11.750  -0.4255   0.05314   0.04670  -0.1190   0.8149   0.0271
 -11.500  -0.4358   0.04996   0.04322  -0.1193   0.8026   0.0273
 -11.250  -0.4435   0.04706   0.04003  -0.1191   0.7911   0.0275
 -11.000  -0.4472   0.04455   0.03721  -0.1186   0.7809   0.0278
 -10.750  -0.4485   0.04219   0.03452  -0.1176   0.7711   0.0282
 -10.500  -0.4482   0.04021   0.03219  -0.1162   0.7616   0.0289
 -10.250  -0.4392   0.03852   0.03034  -0.1153   0.7538   0.0298
 -10.000  -0.4294   0.03727   0.02899  -0.1142   0.7448   0.0308
  -9.750  -0.4181   0.03605   0.02759  -0.1131   0.7379   0.0320
  -9.500  -0.4024   0.03468   0.02604  -0.1122   0.7298   0.0332
  -9.250  -0.3829   0.03329   0.02440  -0.1115   0.7235   0.0345
  -9.000  -0.3624   0.03208   0.02296  -0.1108   0.7166   0.0358
  -8.750  -0.3443   0.03097   0.02186  -0.1100   0.7103   0.0377
  -8.500  -0.3278   0.03011   0.02091  -0.1091   0.7047   0.0400
  -8.250  -0.3102   0.02928   0.01998  -0.1081   0.6982   0.0425
  -8.000  -0.2921   0.02845   0.01901  -0.1069   0.6930   0.0448
  -7.750  -0.2786   0.02758   0.01815  -0.1055   0.6880   0.0475
  -7.500  -0.2639   0.02690   0.01742  -0.1043   0.6825   0.0516
  -7.250  -0.2493   0.02616   0.01659  -0.1030   0.6780   0.0560
  -7.000  -0.2350   0.02541   0.01578  -0.1017   0.6742   0.0612
  -6.750  -0.2206   0.02473   0.01509  -0.1005   0.6691   0.0689
  -6.500  -0.2053   0.02402   0.01435  -0.0994   0.6647   0.0803
  -6.250  -0.1901   0.02317   0.01355  -0.0985   0.6611   0.0993
  -6.000  -0.1752   0.02223   0.01277  -0.0976   0.6573   0.1357
  -5.500  -0.1508   0.01984   0.01168  -0.0957   0.6490   0.3629
  -5.250  -0.1260   0.02018   0.01211  -0.0949   0.6458   0.4547
  -5.000  -0.0998   0.02044   0.01210  -0.0948   0.6427   0.4906
  -4.750  -0.0749   0.02098   0.01259  -0.0939   0.6389   0.5127
  -4.500  -0.0495   0.02149   0.01301  -0.0931   0.6355   0.5320
  -4.250  -0.0237   0.02199   0.01340  -0.0923   0.6326   0.5496
  -4.000   0.0026   0.02244   0.01373  -0.0914   0.6301   0.5633
  -3.750   0.0296   0.02263   0.01376  -0.0911   0.6280   0.5737
  -3.500   0.0538   0.02280   0.01386  -0.0907   0.6247   0.5809
  -3.250   0.0792   0.02276   0.01367  -0.0908   0.6217   0.5872
  -3.000   0.1050   0.02282   0.01365  -0.0906   0.6191   0.5906
  -2.750   0.1315   0.02282   0.01353  -0.0907   0.6167   0.5951
  -2.500   0.1591   0.02272   0.01322  -0.0913   0.6147   0.6002
  -2.250   0.1872   0.02264   0.01299  -0.0917   0.6130   0.6033
  -2.000   0.2122   0.02272   0.01303  -0.0916   0.6104   0.6058
  -1.750   0.2366   0.02280   0.01306  -0.0915   0.6075   0.6085
  -1.500   0.2621   0.02284   0.01303  -0.0917   0.6049   0.6116
  -1.250   0.2888   0.02286   0.01293  -0.0921   0.6026   0.6153
  -1.000   0.3160   0.02288   0.01284  -0.0925   0.6007   0.6186
  -0.750   0.3430   0.02294   0.01284  -0.0927   0.5991   0.6209
  -0.500   0.3709   0.02299   0.01281  -0.0930   0.5977   0.6233
  -0.250   0.3962   0.02315   0.01294  -0.0931   0.5959   0.6261
   0.000   0.4185   0.02344   0.01325  -0.0929   0.5935   0.6294
   0.250   0.4422   0.02370   0.01348  -0.0930   0.5913   0.6328
   0.500   0.4661   0.02395   0.01373  -0.0929   0.5893   0.6351
   0.750   0.4904   0.02419   0.01398  -0.0928   0.5875   0.6374
   1.000   0.5157   0.02441   0.01419  -0.0928   0.5859   0.6401
   1.250   0.5422   0.02459   0.01434  -0.0931   0.5845   0.6431
   1.500   0.5700   0.02473   0.01443  -0.0936   0.5831   0.6466
   1.750   0.5987   0.02487   0.01452  -0.0942   0.5818   0.6503
   2.000   0.6139   0.02555   0.01533  -0.0929   0.5793   0.6533
   2.250   0.6282   0.02631   0.01620  -0.0915   0.5767   0.6567
   2.500   0.6447   0.02700   0.01696  -0.0906   0.5745   0.6604
   2.750   0.6640   0.02757   0.01756  -0.0900   0.5724   0.6645
   3.000   0.6859   0.02799   0.01802  -0.0896   0.5705   0.6680
   3.250   0.7097   0.02832   0.01840  -0.0894   0.5690   0.6718
   3.500   0.7346   0.02866   0.01877  -0.0895   0.5677   0.6762
   3.750   0.7617   0.02896   0.01908  -0.0899   0.5666   0.6814
   4.000   0.7228   0.03219   0.02257  -0.0823   0.5593   0.6849
   4.250   0.7190   0.03383   0.02431  -0.0790   0.5557   0.6895
   4.500   0.7363   0.03452   0.02503  -0.0782   0.5537   0.6955
   4.750   0.7610   0.03487   0.02545  -0.0782   0.5524   0.7013
   5.000   0.7890   0.03509   0.02572  -0.0786   0.5513   0.7079
   5.250   0.8179   0.03535   0.02602  -0.0791   0.5504   0.7153
   5.750   0.6781   0.04936   0.04030  -0.0658   0.5236   0.7261
   6.000   0.7035   0.04965   0.04067  -0.0658   0.5221   0.7347
   6.250   0.7321   0.04970   0.04079  -0.0659   0.5209   0.7448
   6.500   0.7601   0.04977   0.04098  -0.0660   0.5201   0.7552
   7.000   0.7484   0.05528   0.04671  -0.0631   0.5062   0.7789
   7.250   0.7745   0.05548   0.04704  -0.0630   0.5052   0.7969
   7.750   0.7703   0.06017   0.05209  -0.0604   0.4917   0.8505
   8.250   0.7822   0.06361   0.05576  -0.0594   0.4791   1.0000
   8.750   0.8384   0.06396   0.05620  -0.0601   0.4753   1.0000
   9.250   0.8495   0.06808   0.06043  -0.0594   0.4620   1.0000
   9.500   0.8780   0.06813   0.06055  -0.0596   0.4605   1.0000
  10.000   0.8941   0.07159   0.06415  -0.0589   0.4468   1.0000
  10.250   0.9241   0.07127   0.06392  -0.0590   0.4452   1.0000
  10.750   0.9402   0.07468   0.06750  -0.0583   0.4311   1.0000
  12.250   1.0115   0.08221   0.07568  -0.0568   0.3893   1.0000
  12.750   1.0430   0.08357   0.07730  -0.0562   0.3750   1.0000
  13.000   1.0469   0.08572   0.07956  -0.0560   0.3637   1.0000
  13.250   1.0849   0.08300   0.07700  -0.0553   0.3589   1.0000
  13.500   1.0965   0.08386   0.07796  -0.0550   0.3446   1.0000
  13.750   1.1043   0.08539   0.07956  -0.0547   0.3263   1.0000
  14.000   1.1242   0.08522   0.07941  -0.0543   0.3037   1.0000
  14.250   1.1489   0.08432   0.07835  -0.0536   0.2704   1.0000
  14.500   1.1629   0.08490   0.07863  -0.0529   0.2302   1.0000
  14.750   1.1625   0.08762   0.08106  -0.0527   0.1929   1.0000
  15.000   1.1564   0.09138   0.08458  -0.0527   0.1594   1.0000
  15.250   1.1480   0.09559   0.08855  -0.0531   0.1290   1.0000
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