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WORTMANN FX 3 AIRFOIL (fx3-il) Xfoil prediction polar at RE=100,000 Ncrit=0


Details Polar file
Airfoil: WORTMANN FX 3 AIRFOIL (fx3-il)
Reynolds number: 100,000
Max Cl/Cd: 23.37 at α=11.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx3-il-100000.txt
Download as CSV file: xf-fx3-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 3 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5325   0.13449   0.13073  -0.0316   1.0001   0.1634
 -10.000  -0.4936   0.13358   0.12976  -0.0269   1.0001   0.1683
  -9.750  -0.5027   0.13060   0.12679  -0.0267   1.0001   0.1766
  -9.500  -0.5161   0.12652   0.12274  -0.0266   1.0001   0.1839
  -9.250  -0.5262   0.12341   0.11965  -0.0262   1.0001   0.1933
  -9.000  -0.5223   0.12108   0.11732  -0.0243   1.0001   0.2032
  -8.250  -0.9545   0.07064   0.06431  -0.0259   1.0001   0.0692
  -8.000  -0.9497   0.06567   0.05907  -0.0247   1.0001   0.0681
  -7.750  -0.9419   0.06179   0.05476  -0.0236   1.0001   0.0684
  -7.500  -0.9298   0.05878   0.05121  -0.0228   1.0001   0.0695
  -7.250  -0.9146   0.05585   0.04777  -0.0222   1.0001   0.0705
  -7.000  -0.8986   0.05134   0.04295  -0.0215   1.0001   0.0717
  -6.750  -0.8811   0.04919   0.04081  -0.0210   1.0001   0.0751
  -6.500  -0.8617   0.04760   0.03902  -0.0204   1.0001   0.0791
  -6.250  -0.8406   0.04590   0.03693  -0.0196   1.0001   0.0826
  -6.000  -0.8201   0.04407   0.03481  -0.0188   1.0001   0.0872
  -5.750  -0.8009   0.04280   0.03357  -0.0178   1.0001   0.0927
  -5.500  -0.7799   0.04193   0.03249  -0.0169   1.0001   0.0989
  -5.250  -0.7607   0.04083   0.03142  -0.0155   1.0000   0.1052
  -5.000  -0.7356   0.04049   0.03101  -0.0154   0.9985   0.1131
  -4.750  -0.7122   0.04013   0.03070  -0.0146   0.9970   0.1207
  -4.500  -0.6859   0.04022   0.03077  -0.0147   0.9953   0.1300
  -4.250  -0.6638   0.04022   0.03093  -0.0138   0.9940   0.1380
  -4.000  -0.6416   0.04005   0.03074  -0.0132   0.9910   0.1478
  -3.750  -0.6185   0.04011   0.03099  -0.0127   0.9883   0.1593
  -3.500  -0.5919   0.04046   0.03148  -0.0131   0.9860   0.1769
  -3.250  -0.5599   0.03889   0.03216  -0.0172   0.9858   0.4411
  -3.000  -0.5553   0.04561   0.03944  -0.0055   0.9771   0.6770
  -2.750  -0.5429   0.04932   0.04300   0.0018   0.9725   0.7073
  -2.500  -0.5399   0.05166   0.04530   0.0108   0.9690   0.7258
  -2.250  -0.1639   0.06728   0.06017  -0.0250   1.0001   0.9999
  -2.000  -0.1564   0.06685   0.05966  -0.0236   1.0001   0.9999
  -1.750  -0.1488   0.06648   0.05922  -0.0221   1.0001   0.9999
  -1.500  -0.1412   0.06616   0.05884  -0.0205   1.0001   0.9999
  -1.250  -0.1161   0.06562   0.05822  -0.0226   0.9961   0.9999
  -1.000  -0.0837   0.06524   0.05776  -0.0260   0.9877   0.9999
  -0.750  -0.0594   0.06524   0.05768  -0.0278   0.9813   0.9999
  -0.500  -0.0330   0.06520   0.05758  -0.0299   0.9729   0.9999
  -0.250  -0.0162   0.06497   0.05730  -0.0300   0.9648   0.9999
   0.000   0.0087   0.06531   0.05758  -0.0318   0.9581   0.9999
   0.250   0.0214   0.06507   0.05731  -0.0310   0.9496   0.9999
   0.500   0.0453   0.06550   0.05770  -0.0324   0.9432   0.9999
   0.750   0.0551   0.06534   0.05752  -0.0310   0.9350   0.9999
   1.000   0.0780   0.06578   0.05792  -0.0322   0.9284   0.9999
   1.250   0.0866   0.06578   0.05792  -0.0306   0.9208   0.9999
   1.500   0.1080   0.06615   0.05826  -0.0313   0.9135   0.9999
   1.750   0.1347   0.06781   0.05989  -0.0332   0.9103   0.9999
   2.000   0.1359   0.06662   0.05872  -0.0300   0.8984   0.9999
   2.250  -0.0581   0.06325   0.05527   0.0131   0.8804   0.9482
   2.500  -0.0744   0.06198   0.05400   0.0194   0.8703   0.9436
   2.750  -0.1177   0.06160   0.05355   0.0320   0.8640   0.9349
   3.000  -0.1308   0.05977   0.05173   0.0375   0.8533   0.9326
   3.250  -0.1010   0.06106   0.05298   0.0355   0.8493   0.9321
   3.500  -0.1089   0.05992   0.05185   0.0397   0.8399   0.9308
   3.750  -0.0771   0.06105   0.05295   0.0373   0.8350   0.9297
   4.000  -0.0763   0.06059   0.05251   0.0396   0.8264   0.9282
   4.250  -0.0412   0.06170   0.05360   0.0367   0.8206   0.9280
   4.500  -0.0347   0.06162   0.05355   0.0379   0.8120   0.9272
   4.750   0.0083   0.06300   0.05493   0.0337   0.8056   0.9264
   5.000   0.0215   0.06286   0.05482   0.0338   0.7944   0.9253
   5.250   0.0589   0.06236   0.05431   0.0315   0.7732   0.9250
   5.500   0.0971   0.06212   0.05408   0.0289   0.7588   0.9249
   5.750   0.1294   0.06217   0.05417   0.0266   0.7477   0.9243
   6.000   0.1614   0.06238   0.05442   0.0242   0.7376   0.9234
   6.250   0.1965   0.06259   0.05468   0.0215   0.7292   0.9230
   6.500   0.2310   0.06269   0.05484   0.0191   0.7211   0.9228
   6.750   0.2553   0.06290   0.05513   0.0179   0.7107   0.9223
   7.000   0.2883   0.06301   0.05531   0.0156   0.7023   0.9216
   7.250   0.3242   0.06302   0.05542   0.0131   0.6944   0.9208
   7.500   0.3492   0.06333   0.05581   0.0118   0.6838   0.9200
   7.750   0.3947   0.06302   0.05562   0.0083   0.6783   0.9198
   8.000   0.4159   0.06344   0.05614   0.0075   0.6666   0.9194
   8.250   0.4657   0.06280   0.05563   0.0038   0.6622   0.9191
   8.500   0.4866   0.06319   0.05615   0.0031   0.6494   0.9182
   8.750   0.5280   0.06261   0.05571   0.0004   0.6423   0.9174
   9.000   0.5663   0.06171   0.05497  -0.0015   0.6318   0.9167
   9.250   0.6050   0.06026   0.05367  -0.0030   0.6189   0.9160
   9.500   0.6783   0.05564   0.04927  -0.0067   0.6138   0.9156
   9.750   0.7115   0.05442   0.04823  -0.0075   0.6004   0.9148
  10.000   0.7726   0.05082   0.04486  -0.0105   0.5971   0.9145
  10.250   0.8043   0.04962   0.04388  -0.0110   0.5833   0.9141
  10.500   0.8447   0.04761   0.04208  -0.0121   0.5698   0.9140
  10.750   0.8914   0.04511   0.03980  -0.0136   0.5528   0.9138
  11.000   0.9362   0.04268   0.03748  -0.0147   0.5177   0.9133
  11.250   0.9681   0.04142   0.03596  -0.0146   0.4487   0.9127
  11.500   0.9761   0.04242   0.03643  -0.0126   0.3595   0.9118
  11.750   0.9720   0.04474   0.03814  -0.0100   0.2787   0.9109
  12.000   0.9688   0.04733   0.04024  -0.0081   0.2224   0.9100
  12.250   0.9715   0.04967   0.04228  -0.0069   0.1830   0.9092
  12.500   0.9751   0.05180   0.04420  -0.0056   0.1538   0.9086
  12.750   0.9780   0.05400   0.04617  -0.0042   0.1278   0.9080
  13.000   0.9820   0.05622   0.04822  -0.0029   0.1042   0.9075
  13.250   0.9950   0.05785   0.04965  -0.0020   0.0869   0.9070
  13.500   1.0114   0.05932   0.05112  -0.0017   0.0762   0.9066
  13.750   1.0371   0.06040   0.05227  -0.0019   0.0682   0.9063
  14.000   1.0763   0.06119   0.05285  -0.0033   0.0615   0.9062
  14.250   1.0933   0.06294   0.05492  -0.0032   0.0579   0.9058
  14.500   1.1172   0.06460   0.05675  -0.0037   0.0546   0.9055
  14.750   1.1652   0.06663   0.05871  -0.0063   0.0512   0.9056
  15.000   1.1686   0.06934   0.06184  -0.0051   0.0501   0.9053
  15.250   1.1708   0.07236   0.06525  -0.0040   0.0488   0.9050
  15.500   1.1712   0.07564   0.06888  -0.0030   0.0477   0.9048
  15.750   1.1681   0.07932   0.07290  -0.0020   0.0472   0.9045
  16.000   1.1598   0.08344   0.07738  -0.0009   0.0469   0.9041
  16.250   1.1463   0.08802   0.08232   0.0000   0.0469   0.9036
  16.500   1.1290   0.09309   0.08773   0.0005   0.0471   0.9031
  16.750   1.1081   0.09872   0.09370   0.0003   0.0474   0.9024
  17.000   1.0845   0.10493   0.10023  -0.0006   0.0477   0.9017
  17.250   1.0591   0.11185   0.10744  -0.0027   0.0482   0.9009
  17.500   1.0323   0.11955   0.11541  -0.0059   0.0487   0.9001
  17.750   1.0053   0.12807   0.12417  -0.0104   0.0494   0.8994
  18.000   0.9799   0.13721   0.13349  -0.0160   0.0500   0.8986
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