Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

FX 66-S-196 V1 AIRFOIL (fx66196v-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: FX 66-S-196 V1 AIRFOIL (fx66196v-il)
Reynolds number: 1,000,000
Max Cl/Cd: 138.96 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx66196v-il-1000000.txt
Download as CSV file: xf-fx66196v-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.000  -0.6236   0.10159   0.09948  -0.0616   1.0000   0.0087
 -16.750  -0.6450   0.09298   0.09074  -0.0666   1.0000   0.0087
 -16.500  -0.6748   0.08351   0.08111  -0.0721   1.0000   0.0086
 -16.250  -0.6950   0.07613   0.07357  -0.0765   1.0000   0.0086
 -16.000  -0.7070   0.06938   0.06667  -0.0810   0.9626   0.0086
 -15.750  -0.6933   0.06170   0.05870  -0.0929   0.9397   0.0087
 -15.500  -0.6706   0.05461   0.05130  -0.1058   0.9196   0.0087
 -15.250  -0.6601   0.04787   0.04415  -0.1164   0.8908   0.0090
 -15.000  -0.6538   0.04435   0.04033  -0.1202   0.8589   0.0090
 -14.750  -0.6527   0.04170   0.03749  -0.1215   0.8327   0.0093
 -14.500  -0.6524   0.03932   0.03493  -0.1220   0.8150   0.0093
 -14.250  -0.6504   0.03727   0.03271  -0.1222   0.7974   0.0093
 -14.000  -0.6440   0.03566   0.03101  -0.1224   0.7821   0.0096
 -13.750  -0.6384   0.03406   0.02928  -0.1223   0.7672   0.0096
 -13.250  -0.6257   0.03105   0.02605  -0.1219   0.7419   0.0099
 -13.000  -0.6191   0.02962   0.02450  -0.1214   0.7307   0.0100
 -12.750  -0.6084   0.02856   0.02335  -0.1212   0.7200   0.0103
 -12.500  -0.6013   0.02723   0.02192  -0.1205   0.7099   0.0104
 -12.250  -0.5917   0.02610   0.02069  -0.1199   0.7008   0.0106
 -12.000  -0.5817   0.02506   0.01956  -0.1192   0.6915   0.0109
 -11.750  -0.5703   0.02409   0.01850  -0.1186   0.6835   0.0111
 -11.250  -0.5451   0.02244   0.01669  -0.1172   0.6673   0.0115
 -10.750  -0.5384   0.01975   0.01381  -0.1139   0.6533   0.0120
 -10.500  -0.5323   0.01874   0.01273  -0.1122   0.6464   0.0121
 -10.250  -0.5266   0.01788   0.01182  -0.1103   0.6405   0.0125
 -10.000  -0.5223   0.01727   0.01115  -0.1076   0.6345   0.0127
  -9.750  -0.5081   0.01679   0.01060  -0.1062   0.6286   0.0131
  -9.500  -0.4918   0.01627   0.01003  -0.1051   0.6236   0.0135
  -9.250  -0.4742   0.01577   0.00947  -0.1041   0.6181   0.0139
  -9.000  -0.4549   0.01537   0.00898  -0.1032   0.6127   0.0143
  -8.750  -0.4331   0.01501   0.00857  -0.1027   0.6082   0.0147
  -8.500  -0.4166   0.01426   0.00776  -0.1017   0.6034   0.0156
  -8.250  -0.3949   0.01387   0.00732  -0.1011   0.5986   0.0164
  -8.000  -0.3714   0.01355   0.00695  -0.1008   0.5945   0.0173
  -7.750  -0.3468   0.01327   0.00663  -0.1007   0.5905   0.0182
  -7.500  -0.3236   0.01288   0.00618  -0.1003   0.5864   0.0194
  -7.250  -0.2999   0.01254   0.00580  -0.1001   0.5823   0.0210
  -7.000  -0.2742   0.01227   0.00550  -0.1001   0.5792   0.0225
  -6.750  -0.2488   0.01195   0.00514  -0.1000   0.5760   0.0246
  -6.500  -0.2231   0.01166   0.00484  -0.1000   0.5727   0.0275
  -6.250  -0.1974   0.01141   0.00455  -0.0999   0.5695   0.0316
  -6.000  -0.1715   0.01120   0.00431  -0.0999   0.5659   0.0370
  -5.750  -0.1450   0.01087   0.00404  -0.1001   0.5639   0.0482
  -5.500  -0.1185   0.01054   0.00379  -0.1002   0.5615   0.0658
  -5.250  -0.0927   0.01014   0.00351  -0.1004   0.5589   0.0994
  -5.000  -0.0672   0.00967   0.00323  -0.1005   0.5562   0.1514
  -4.750  -0.0426   0.00908   0.00291  -0.1006   0.5537   0.2283
  -4.500  -0.0192   0.00832   0.00254  -0.1007   0.5508   0.3392
  -4.250   0.0068   0.00789   0.00243  -0.1008   0.5491   0.4379
  -4.000   0.0358   0.00787   0.00240  -0.1012   0.5473   0.4569
  -3.750   0.0649   0.00787   0.00240  -0.1016   0.5454   0.4706
  -3.500   0.0940   0.00789   0.00239  -0.1019   0.5434   0.4791
  -3.250   0.1231   0.00795   0.00240  -0.1023   0.5415   0.4876
  -3.000   0.1518   0.00798   0.00240  -0.1026   0.5395   0.4946
  -2.750   0.1805   0.00807   0.00244  -0.1028   0.5374   0.5020
  -2.500   0.2091   0.00817   0.00248  -0.1031   0.5351   0.5085
  -2.250   0.2381   0.00818   0.00250  -0.1035   0.5340   0.5143
  -2.000   0.2673   0.00822   0.00253  -0.1039   0.5327   0.5190
  -1.750   0.2964   0.00828   0.00254  -0.1043   0.5313   0.5221
  -1.500   0.3252   0.00825   0.00251  -0.1046   0.5298   0.5250
  -1.250   0.3540   0.00825   0.00251  -0.1050   0.5284   0.5272
  -1.000   0.3828   0.00828   0.00251  -0.1053   0.5269   0.5292
  -0.750   0.4115   0.00831   0.00252  -0.1057   0.5255   0.5310
  -0.500   0.4402   0.00835   0.00254  -0.1060   0.5241   0.5328
  -0.250   0.4687   0.00842   0.00257  -0.1063   0.5225   0.5348
   0.000   0.4973   0.00851   0.00262  -0.1067   0.5208   0.5364
   0.250   0.5261   0.00857   0.00266  -0.1071   0.5196   0.5376
   0.500   0.5548   0.00858   0.00267  -0.1075   0.5188   0.5391
   0.750   0.5834   0.00858   0.00270  -0.1078   0.5179   0.5411
   1.000   0.6120   0.00860   0.00274  -0.1082   0.5170   0.5429
   1.250   0.6406   0.00864   0.00279  -0.1085   0.5160   0.5448
   1.500   0.6691   0.00868   0.00284  -0.1089   0.5150   0.5466
   1.750   0.6977   0.00873   0.00289  -0.1093   0.5139   0.5486
   2.000   0.7262   0.00879   0.00295  -0.1096   0.5128   0.5506
   2.250   0.7546   0.00884   0.00301  -0.1100   0.5118   0.5525
   2.500   0.7830   0.00891   0.00308  -0.1103   0.5108   0.5543
   2.750   0.8111   0.00895   0.00315  -0.1106   0.5098   0.5571
   3.000   0.8393   0.00902   0.00324  -0.1109   0.5089   0.5596
   3.250   0.8675   0.00910   0.00334  -0.1113   0.5079   0.5622
   3.500   0.8958   0.00922   0.00346  -0.1117   0.5068   0.5650
   3.750   0.9244   0.00938   0.00362  -0.1121   0.5053   0.5678
   4.000   0.9527   0.00948   0.00374  -0.1125   0.5043   0.5705
   4.250   0.9804   0.00950   0.00384  -0.1127   0.5037   0.5741
   4.500   1.0082   0.00956   0.00395  -0.1130   0.5030   0.5775
   4.750   1.0360   0.00963   0.00406  -0.1133   0.5023   0.5812
   5.000   1.0638   0.00971   0.00419  -0.1136   0.5015   0.5846
   5.250   1.0913   0.00977   0.00431  -0.1138   0.5005   0.5887
   5.500   1.1187   0.00983   0.00443  -0.1140   0.4994   0.5932
   5.750   1.1462   0.00991   0.00456  -0.1142   0.4983   0.5981
   6.000   1.1735   0.00998   0.00467  -0.1144   0.4970   0.6030
   6.250   1.2006   0.01005   0.00480  -0.1146   0.4958   0.6087
   6.500   1.2277   0.01013   0.00493  -0.1148   0.4945   0.6148
   6.750   1.2545   0.01021   0.00506  -0.1149   0.4929   0.6211
   7.000   1.2818   0.01036   0.00525  -0.1152   0.4908   0.6283
   7.250   1.3081   0.01048   0.00544  -0.1152   0.4886   0.6357
   7.500   1.3298   0.01032   0.00540  -0.1142   0.4842   0.6441
   7.750   1.3501   0.01022   0.00530  -0.1130   0.4761   0.6530
   8.000   1.3713   0.01015   0.00533  -0.1119   0.4687   0.6633
   8.250   1.3901   0.01022   0.00541  -0.1105   0.4595   0.6744
   8.500   1.4130   0.01023   0.00553  -0.1098   0.4525   0.6867
   8.750   1.4317   0.01036   0.00570  -0.1084   0.4464   0.7003
   9.000   1.4507   0.01044   0.00588  -0.1070   0.4387   0.7155
   9.250   1.4649   0.01063   0.00612  -0.1047   0.4269   0.7328
   9.500   1.4683   0.01109   0.00653  -0.1006   0.3949   0.7536
   9.750   1.4521   0.01224   0.00753  -0.0934   0.3563   0.7799
  10.000   1.4310   0.01377   0.00898  -0.0862   0.3189   0.8183
  10.250   1.4171   0.01551   0.01082  -0.0813   0.2848   0.9151
  10.500   1.4184   0.01967   0.01474  -0.0837   0.2234   1.0000
  10.750   1.4072   0.02296   0.01788  -0.0819   0.1920   1.0000
  11.000   1.3915   0.02681   0.02160  -0.0801   0.1609   1.0000
  11.250   1.3795   0.03039   0.02509  -0.0786   0.1382   1.0000
  11.500   1.3618   0.03446   0.02906  -0.0769   0.1131   1.0000
  11.750   1.3484   0.03824   0.03275  -0.0754   0.0919   1.0000
  12.000   1.3384   0.04178   0.03622  -0.0742   0.0743   1.0000
  12.250   1.3299   0.04522   0.03960  -0.0731   0.0581   1.0000
  12.500   1.3231   0.04853   0.04285  -0.0722   0.0448   1.0000
  12.750   1.3200   0.05152   0.04580  -0.0714   0.0341   1.0000
  13.000   1.3176   0.05447   0.04872  -0.0707   0.0256   1.0000
  13.250   1.3168   0.05728   0.05151  -0.0700   0.0199   1.0000
  13.500   1.3193   0.05978   0.05402  -0.0695   0.0165   1.0000
  13.750   1.3217   0.06234   0.05660  -0.0691   0.0147   1.0000
  14.000   1.3269   0.06460   0.05889  -0.0688   0.0135   1.0000
  14.250   1.3319   0.06687   0.06119  -0.0684   0.0124   1.0000
  14.500   1.3324   0.06965   0.06401  -0.0680   0.0113   1.0000
  14.750   1.3392   0.07178   0.06618  -0.0678   0.0108   1.0000
  15.000   1.3448   0.07405   0.06851  -0.0676   0.0102   1.0000
  15.250   1.3488   0.07650   0.07099  -0.0674   0.0096   1.0000
  15.500   1.3527   0.07893   0.07346  -0.0671   0.0092   1.0000
  15.750   1.3522   0.08188   0.07646  -0.0668   0.0087   1.0000
  16.000   1.3555   0.08444   0.07908  -0.0667   0.0084   1.0000
  16.250   1.3612   0.08671   0.08140  -0.0666   0.0081   1.0000
  16.500   1.3649   0.08925   0.08399  -0.0665   0.0077   1.0000
  16.750   1.3676   0.09186   0.08665  -0.0664   0.0075   1.0000
  17.000   1.3708   0.09440   0.08923  -0.0663   0.0072   1.0000
  17.250   1.3724   0.09719   0.09208  -0.0663   0.0070   1.0000
  17.500   1.3706   0.10038   0.09532  -0.0663   0.0067   1.0000
  17.750   1.3673   0.10378   0.09879  -0.0663   0.0065   1.0000
<< Back to FX 66-S-196 V1 AIRFOIL (fx66196v-il)

Polar data table (+)

Polar graphs


<< Back to FX 66-S-196 V1 AIRFOIL (fx66196v-il)