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FX 60-100 (126) AIRFOIL (fx601001-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: FX 60-100 (126) AIRFOIL (fx601001-il)
Reynolds number: 500,000
Max Cl/Cd: 92.37 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx601001-il-500000-n5.txt
Download as CSV file: xf-fx601001-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 60-100 (126) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4186   0.08234   0.08015  -0.0405   1.0000   0.0060
  -9.250  -0.4339   0.07589   0.07376  -0.0429   1.0000   0.0059
  -9.000  -0.5390   0.04476   0.04252  -0.0652   0.9927   0.0052
  -8.750  -0.5115   0.02998   0.02687  -0.0938   0.9814   0.0051
  -8.500  -0.4781   0.02548   0.02187  -0.1010   0.9774   0.0052
  -8.250  -0.4478   0.02278   0.01883  -0.1045   0.9712   0.0054
  -8.000  -0.4151   0.02052   0.01626  -0.1076   0.9667   0.0055
  -7.750  -0.3859   0.01884   0.01433  -0.1093   0.9614   0.0058
  -7.500  -0.3557   0.01737   0.01263  -0.1108   0.9566   0.0061
  -7.250  -0.3240   0.01609   0.01114  -0.1124   0.9527   0.0064
  -7.000  -0.2963   0.01506   0.00994  -0.1129   0.9457   0.0067
  -6.750  -0.2661   0.01417   0.00890  -0.1138   0.9401   0.0070
  -6.500  -0.2375   0.01352   0.00812  -0.1143   0.9334   0.0072
  -6.250  -0.2085   0.01236   0.00678  -0.1151   0.9266   0.0082
  -6.000  -0.1800   0.01176   0.00610  -0.1155   0.9193   0.0089
  -5.750  -0.1509   0.01121   0.00544  -0.1159   0.9115   0.0096
  -5.500  -0.1224   0.01073   0.00485  -0.1162   0.9026   0.0104
  -5.250  -0.0935   0.01033   0.00433  -0.1164   0.8938   0.0113
  -5.000  -0.0649   0.01000   0.00390  -0.1165   0.8844   0.0123
  -4.750  -0.0360   0.00960   0.00337  -0.1167   0.8752   0.0171
  -4.500  -0.0073   0.00927   0.00304  -0.1169   0.8662   0.0270
  -4.250   0.0211   0.00903   0.00282  -0.1171   0.8563   0.0446
  -4.000   0.0494   0.00887   0.00262  -0.1172   0.8463   0.0543
  -3.750   0.0778   0.00873   0.00242  -0.1172   0.8363   0.0616
  -3.500   0.1061   0.00855   0.00222  -0.1173   0.8265   0.0761
  -3.250   0.1348   0.00823   0.00201  -0.1177   0.8168   0.1151
  -3.000   0.1635   0.00790   0.00181  -0.1180   0.8072   0.1763
  -2.500   0.2206   0.00737   0.00151  -0.1186   0.7863   0.2897
  -2.250   0.2491   0.00711   0.00144  -0.1189   0.7759   0.3675
  -2.000   0.2773   0.00708   0.00148  -0.1189   0.7651   0.4170
  -1.500   0.3333   0.00721   0.00151  -0.1186   0.7400   0.4564
  -1.250   0.3611   0.00731   0.00151  -0.1184   0.7236   0.4664
  -1.000   0.3886   0.00743   0.00152  -0.1182   0.7030   0.4769
  -0.750   0.4158   0.00755   0.00155  -0.1179   0.6818   0.4854
  -0.500   0.4434   0.00767   0.00155  -0.1177   0.6636   0.4908
  -0.250   0.4710   0.00776   0.00156  -0.1176   0.6475   0.4944
   0.000   0.4984   0.00785   0.00159  -0.1174   0.6312   0.4980
   0.250   0.5259   0.00796   0.00162  -0.1172   0.6150   0.5013
   0.500   0.5535   0.00808   0.00166  -0.1171   0.5997   0.5049
   0.750   0.5809   0.00819   0.00170  -0.1170   0.5839   0.5076
   1.000   0.6082   0.00830   0.00176  -0.1168   0.5680   0.5105
   1.250   0.6357   0.00840   0.00182  -0.1167   0.5550   0.5139
   1.500   0.6635   0.00849   0.00190  -0.1166   0.5454   0.5170
   1.750   0.6911   0.00860   0.00197  -0.1165   0.5355   0.5194
   2.000   0.7189   0.00868   0.00205  -0.1165   0.5252   0.5213
   2.250   0.7465   0.00876   0.00215  -0.1164   0.5147   0.5233
   2.500   0.7739   0.00887   0.00225  -0.1163   0.5025   0.5253
   2.750   0.8012   0.00899   0.00236  -0.1161   0.4872   0.5272
   3.000   0.8283   0.00913   0.00249  -0.1160   0.4687   0.5292
   3.250   0.8550   0.00931   0.00262  -0.1157   0.4470   0.5316
   3.500   0.8812   0.00954   0.00277  -0.1155   0.4190   0.5338
   3.750   0.9069   0.00985   0.00297  -0.1151   0.3867   0.5359
   4.000   0.9320   0.01022   0.00323  -0.1147   0.3524   0.5379
   4.250   0.9574   0.01056   0.00349  -0.1144   0.3254   0.5401
   4.500   0.9828   0.01090   0.00377  -0.1140   0.3004   0.5427
   4.750   1.0077   0.01131   0.00407  -0.1136   0.2689   0.5456
   5.000   1.0306   0.01197   0.00448  -0.1130   0.2180   0.5484
   5.250   1.0542   0.01252   0.00487  -0.1125   0.1802   0.5512
   5.500   1.0787   0.01295   0.00523  -0.1120   0.1584   0.5543
   5.750   1.1029   0.01342   0.00561  -0.1115   0.1343   0.5578
   6.000   1.1238   0.01428   0.00618  -0.1107   0.0826   0.5617
   6.250   1.1443   0.01519   0.00689  -0.1097   0.0420   0.5661
   6.500   1.1653   0.01603   0.00765  -0.1088   0.0166   0.5719
   7.000   1.2122   0.01705   0.00883  -0.1074   0.0098   0.5879
   7.250   1.2354   0.01754   0.00945  -0.1067   0.0088   0.6005
   7.500   1.2578   0.01809   0.01015  -0.1060   0.0080   0.6211
   7.750   1.2792   0.01873   0.01096  -0.1050   0.0072   0.6555
   8.000   1.2978   0.01966   0.01213  -0.1037   0.0065   0.7060
   8.250   1.3185   0.02017   0.01288  -0.1027   0.0061   0.7767
   8.500   1.3330   0.02046   0.01351  -0.1002   0.0057   1.0000
   8.750   1.3523   0.02124   0.01436  -0.0990   0.0053   1.0000
   9.000   1.3701   0.02211   0.01531  -0.0977   0.0050   1.0000
   9.250   1.3869   0.02303   0.01630  -0.0962   0.0048   1.0000
   9.500   1.4020   0.02402   0.01742  -0.0945   0.0045   1.0000
   9.750   1.4137   0.02518   0.01867  -0.0924   0.0043   1.0000
  10.000   1.4177   0.02666   0.02025  -0.0891   0.0042   1.0000
  10.250   1.4219   0.02810   0.02181  -0.0861   0.0041   1.0000
  10.500   1.4285   0.02943   0.02326  -0.0835   0.0040   1.0000
  10.750   1.4341   0.03091   0.02487  -0.0811   0.0039   1.0000
  11.000   1.4381   0.03261   0.02670  -0.0787   0.0038   1.0000
  11.250   1.4415   0.03446   0.02870  -0.0766   0.0037   1.0000
  11.500   1.4443   0.03647   0.03084  -0.0747   0.0036   1.0000
  11.750   1.4469   0.03859   0.03311  -0.0731   0.0035   1.0000
  12.000   1.4487   0.04089   0.03555  -0.0717   0.0034   1.0000
  12.250   1.4506   0.04328   0.03808  -0.0707   0.0032   1.0000
  12.500   1.4516   0.04587   0.04081  -0.0699   0.0031   1.0000
  12.750   1.4519   0.04864   0.04371  -0.0694   0.0030   1.0000
  13.000   1.4506   0.05178   0.04698  -0.0691   0.0030   1.0000
  13.250   1.4492   0.05504   0.05036  -0.0692   0.0029   1.0000
  13.500   1.4455   0.05880   0.05426  -0.0696   0.0028   1.0000
  13.750   1.4408   0.06288   0.05848  -0.0704   0.0028   1.0000
  14.000   1.4340   0.06745   0.06320  -0.0715   0.0028   1.0000
  14.250   1.4265   0.07235   0.06825  -0.0730   0.0027   1.0000
  14.500   1.4180   0.07767   0.07372  -0.0750   0.0027   1.0000
  14.750   1.4076   0.08356   0.07976  -0.0773   0.0027   1.0000
  15.000   1.3962   0.08988   0.08625  -0.0801   0.0027   1.0000
  15.250   1.3843   0.09661   0.09313  -0.0833   0.0026   1.0000
  15.500   1.3712   0.10387   0.10055  -0.0870   0.0026   1.0000
  15.750   1.3580   0.11144   0.10828  -0.0910   0.0026   1.0000
  16.000   1.3446   0.11938   0.11638  -0.0954   0.0026   1.0000
  16.250   1.3308   0.12763   0.12479  -0.1002   0.0026   1.0000
  16.500   1.3173   0.13608   0.13339  -0.1051   0.0026   1.0000
  16.750   1.3039   0.14469   0.14214  -0.1104   0.0026   1.0000
  17.000   1.2909   0.15351   0.15111  -0.1158   0.0026   1.0000
  17.250   1.2770   0.16291   0.16066  -0.1218   0.0026   1.0000
  17.500   1.2614   0.17316   0.17106  -0.1283   0.0027   1.0000
  17.750   1.2476   0.18332   0.18134  -0.1348   0.0027   1.0000
  18.000   1.2255   0.19723   0.19543  -0.1436   0.0027   1.0000
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