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FX 60-100 AIRFOIL (fx60100-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 60-100 AIRFOIL (fx60100-il)
Reynolds number: 200,000
Max Cl/Cd: 77.73 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx60100-il-200000-n5.txt
Download as CSV file: xf-fx60100-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 60-100 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3829   0.08107   0.07762  -0.0424   1.0000   0.0135
  -8.500  -0.3901   0.07762   0.07426  -0.0425   1.0000   0.0133
  -8.250  -0.3999   0.07461   0.07132  -0.0420   1.0000   0.0131
  -8.000  -0.4163   0.07201   0.06881  -0.0402   1.0000   0.0129
  -7.750  -0.4233   0.06663   0.06350  -0.0440   0.9959   0.0127
  -7.500  -0.4056   0.05043   0.04708  -0.0696   0.9844   0.0121
  -7.250  -0.3833   0.04070   0.03680  -0.0851   0.9750   0.0117
  -7.000  -0.3522   0.03355   0.02897  -0.0943   0.9707   0.0113
  -6.750  -0.3241   0.02900   0.02382  -0.0984   0.9648   0.0112
  -6.500  -0.2910   0.02558   0.01983  -0.1017   0.9610   0.0112
  -6.250  -0.2558   0.02299   0.01679  -0.1044   0.9583   0.0114
  -6.000  -0.2199   0.02097   0.01442  -0.1068   0.9561   0.0118
  -5.750  -0.1916   0.01956   0.01278  -0.1072   0.9500   0.0122
  -5.500  -0.1583   0.01868   0.01168  -0.1085   0.9460   0.0135
  -5.250  -0.1239   0.01712   0.00998  -0.1103   0.9427   0.0144
  -5.000  -0.0940   0.01606   0.00885  -0.1110   0.9366   0.0147
  -4.750  -0.0618   0.01516   0.00786  -0.1121   0.9316   0.0153
  -4.500  -0.0275   0.01440   0.00699  -0.1136   0.9280   0.0161
  -4.250   0.0020   0.01383   0.00629  -0.1141   0.9212   0.0171
  -4.000   0.0346   0.01331   0.00561  -0.1150   0.9156   0.0187
  -3.750   0.0658   0.01280   0.00502  -0.1156   0.9097   0.0227
  -3.500   0.0964   0.01211   0.00450  -0.1164   0.9033   0.0704
  -3.250   0.1288   0.01104   0.00406  -0.1181   0.8988   0.2233
  -3.000   0.1569   0.01057   0.00403  -0.1185   0.8913   0.3510
  -2.750   0.1871   0.01044   0.00391  -0.1188   0.8855   0.3903
  -2.500   0.2154   0.01037   0.00380  -0.1187   0.8774   0.4108
  -2.250   0.2450   0.01029   0.00366  -0.1187   0.8703   0.4338
  -2.000   0.2728   0.01025   0.00360  -0.1185   0.8612   0.4544
  -1.750   0.3018   0.01020   0.00353  -0.1184   0.8544   0.4738
  -1.500   0.3296   0.01017   0.00348  -0.1182   0.8452   0.4892
  -1.250   0.3577   0.01013   0.00341  -0.1180   0.8358   0.5031
  -1.000   0.3861   0.01009   0.00333  -0.1178   0.8264   0.5158
  -0.750   0.4137   0.01008   0.00330  -0.1175   0.8155   0.5283
  -0.500   0.4416   0.01007   0.00327  -0.1173   0.8053   0.5406
  -0.250   0.4695   0.01005   0.00323  -0.1170   0.7944   0.5511
   0.000   0.4972   0.01004   0.00319  -0.1167   0.7822   0.5608
   0.250   0.5247   0.01004   0.00318  -0.1164   0.7695   0.5722
   0.500   0.5522   0.01005   0.00319  -0.1161   0.7562   0.5843
   0.750   0.5795   0.01007   0.00319  -0.1158   0.7414   0.5960
   1.000   0.6066   0.01010   0.00319  -0.1154   0.7240   0.6071
   1.250   0.6332   0.01014   0.00321  -0.1149   0.7030   0.6186
   1.500   0.6598   0.01021   0.00322  -0.1143   0.6813   0.6304
   1.750   0.6860   0.01031   0.00326  -0.1138   0.6564   0.6425
   2.000   0.7119   0.01043   0.00332  -0.1132   0.6299   0.6560
   2.250   0.7377   0.01057   0.00343  -0.1126   0.6061   0.6715
   2.500   0.7633   0.01072   0.00355  -0.1120   0.5831   0.6892
   2.750   0.7886   0.01088   0.00370  -0.1114   0.5594   0.7085
   3.000   0.8132   0.01107   0.00387  -0.1106   0.5335   0.7300
   3.500   0.8605   0.01143   0.00422  -0.1087   0.4813   0.7945
   3.750   0.8793   0.01139   0.00433  -0.1065   0.4585   0.8900
   4.000   0.9055   0.01165   0.00455  -0.1062   0.4335   1.0000
   4.250   0.9308   0.01201   0.00481  -0.1058   0.4083   1.0000
   4.500   0.9562   0.01237   0.00509  -0.1054   0.3827   1.0000
   4.750   0.9806   0.01281   0.00541  -0.1049   0.3536   1.0000
   5.000   1.0049   0.01326   0.00578  -0.1044   0.3246   1.0000
   5.250   1.0288   0.01376   0.00617  -0.1039   0.2955   1.0000
   5.500   1.0521   0.01431   0.00660  -0.1032   0.2645   1.0000
   5.750   1.0743   0.01496   0.00709  -0.1025   0.2277   1.0000
   6.000   1.0959   0.01571   0.00765  -0.1017   0.1885   1.0000
   6.250   1.1175   0.01644   0.00823  -0.1010   0.1585   1.0000
   6.500   1.1394   0.01714   0.00882  -0.1002   0.1359   1.0000
   6.750   1.1616   0.01778   0.00943  -0.0995   0.1217   1.0000
   7.000   1.1840   0.01839   0.01005  -0.0988   0.1073   1.0000
   7.250   1.2055   0.01907   0.01073  -0.0979   0.0955   1.0000
   7.500   1.2258   0.01985   0.01147  -0.0970   0.0859   1.0000
   7.750   1.2476   0.02046   0.01217  -0.0961   0.0763   1.0000
   8.000   1.2681   0.02117   0.01292  -0.0951   0.0684   1.0000
   8.250   1.2873   0.02199   0.01372  -0.0940   0.0623   1.0000
   8.500   1.3064   0.02276   0.01461  -0.0928   0.0582   1.0000
   8.750   1.3238   0.02367   0.01556  -0.0914   0.0545   1.0000
   9.000   1.3381   0.02480   0.01674  -0.0897   0.0505   1.0000
   9.250   1.3572   0.02547   0.01757  -0.0886   0.0471   1.0000
   9.500   1.3745   0.02623   0.01843  -0.0873   0.0428   1.0000
   9.750   1.3877   0.02718   0.01941  -0.0854   0.0393   1.0000
  10.000   1.4038   0.02788   0.02025  -0.0839   0.0361   1.0000
  10.250   1.4174   0.02874   0.02119  -0.0822   0.0333   1.0000
  10.500   1.4282   0.02982   0.02228  -0.0803   0.0302   1.0000
  10.750   1.4418   0.03071   0.02335  -0.0787   0.0275   1.0000
  11.000   1.4536   0.03176   0.02450  -0.0770   0.0238   1.0000
  11.250   1.4631   0.03303   0.02588  -0.0753   0.0206   1.0000
  11.500   1.4723   0.03438   0.02733  -0.0736   0.0160   1.0000
  11.750   1.4785   0.03605   0.02909  -0.0718   0.0116   1.0000
  12.000   1.4816   0.03807   0.03117  -0.0700   0.0093   1.0000
  12.250   1.4827   0.04035   0.03354  -0.0683   0.0079   1.0000
  12.500   1.4824   0.04287   0.03618  -0.0669   0.0070   1.0000
  12.750   1.4825   0.04544   0.03894  -0.0657   0.0065   1.0000
  13.000   1.4809   0.04832   0.04200  -0.0648   0.0060   1.0000
  13.250   1.4778   0.05151   0.04538  -0.0642   0.0057   1.0000
  13.500   1.4729   0.05508   0.04914  -0.0640   0.0055   1.0000
  13.750   1.4662   0.05908   0.05333  -0.0642   0.0054   1.0000
  14.000   1.4576   0.06358   0.05804  -0.0650   0.0052   1.0000
  14.250   1.4471   0.06862   0.06328  -0.0663   0.0051   1.0000
  14.500   1.4352   0.07420   0.06909  -0.0682   0.0051   1.0000
  14.750   1.4218   0.08039   0.07549  -0.0707   0.0050   1.0000
  15.000   1.4067   0.08727   0.08258  -0.0738   0.0050   1.0000
  15.250   1.3910   0.09465   0.09016  -0.0775   0.0050   1.0000
  15.500   1.3736   0.10276   0.09847  -0.0818   0.0049   1.0000
  15.750   1.3560   0.11128   0.10720  -0.0865   0.0050   1.0000
  16.000   1.3376   0.12038   0.11650  -0.0918   0.0050   1.0000
  16.250   1.3170   0.13041   0.12669  -0.0977   0.0051   1.0000
  16.500   1.2969   0.14073   0.13719  -0.1039   0.0052   1.0000
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