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FX 84-W-218 (fx84w218-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 84-W-218 (fx84w218-il)
Reynolds number: 50,000
Max Cl/Cd: 6.7 at α=10.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx84w218-il-50000-n5.txt
Download as CSV file: xf-fx84w218-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 84-W-218                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.2800   0.12539   0.11745  -0.0752   0.9707   0.1159
 -13.500  -0.2728   0.12044   0.11245  -0.0794   0.9665   0.1183
 -13.000  -0.3000   0.10471   0.09664  -0.0899   0.9570   0.1245
 -12.750  -0.2804   0.10211   0.09400  -0.0928   0.9526   0.1275
 -12.500  -0.3903   0.07957   0.07124  -0.1057   0.9486   0.1326
 -12.250  -0.4991   0.06443   0.05559  -0.1132   0.9382   0.1335
 -12.000  -0.5168   0.05997   0.05088  -0.1153   0.9311   0.1358
 -11.750  -0.4991   0.05888   0.04981  -0.1157   0.9239   0.1390
 -11.500  -0.5013   0.05587   0.04658  -0.1172   0.9178   0.1424
 -11.250  -0.5232   0.05343   0.04389  -0.1151   0.9072   0.1449
 -11.000  -0.5217   0.05130   0.04156  -0.1150   0.9009   0.1484
 -10.750  -0.5139   0.05068   0.04096  -0.1133   0.8927   0.1516
 -10.500  -0.5118   0.04936   0.03951  -0.1119   0.8853   0.1556
 -10.250  -0.5223   0.04796   0.03784  -0.1089   0.8773   0.1593
 -10.000  -0.5170   0.04738   0.03727  -0.1066   0.8694   0.1630
  -9.750  -0.5019   0.04650   0.03635  -0.1058   0.8641   0.1681
  -9.500  -0.5122   0.04593   0.03563  -0.1014   0.8553   0.1719
  -9.250  -0.5093   0.04523   0.03485  -0.0987   0.8481   0.1766
  -9.000  -0.4885   0.04450   0.03412  -0.0984   0.8436   0.1829
  -8.750  -0.4956   0.04414   0.03361  -0.0940   0.8354   0.1877
  -8.500  -0.4881   0.04368   0.03314  -0.0916   0.8285   0.1933
  -8.250  -0.4704   0.04301   0.03243  -0.0907   0.8239   0.2011
  -8.000  -0.4617   0.04248   0.03181  -0.0885   0.8182   0.2084
  -7.750  -0.4651   0.04249   0.03187  -0.0842   0.8097   0.2136
  -7.500  -0.4525   0.04187   0.03107  -0.0825   0.8045   0.2230
  -7.250  -0.4270   0.04130   0.03059  -0.0825   0.8010   0.2333
  -7.000  -0.4395   0.04142   0.03064  -0.0769   0.7918   0.2394
  -6.750  -0.4282   0.04114   0.03043  -0.0748   0.7858   0.2485
  -6.500  -0.4085   0.04060   0.02980  -0.0739   0.7818   0.2616
  -6.250  -0.3828   0.04004   0.02926  -0.0738   0.7788   0.2762
  -6.000  -0.4044   0.04050   0.02974  -0.0669   0.7678   0.2813
  -5.750  -0.3885   0.04018   0.02945  -0.0653   0.7629   0.2954
  -5.500  -0.3646   0.03972   0.02905  -0.0649   0.7595   0.3125
  -5.250  -0.3715   0.03991   0.02926  -0.0601   0.7517   0.3230
  -5.000  -0.3687   0.03988   0.02925  -0.0566   0.7447   0.3374
  -4.750  -0.3482   0.03959   0.02902  -0.0556   0.7405   0.3574
  -4.500  -0.3213   0.03922   0.02870  -0.0554   0.7377   0.3814
  -4.250  -0.3379   0.03975   0.02934  -0.0493   0.7281   0.3916
  -4.000  -0.3247   0.03972   0.02940  -0.0472   0.7226   0.4132
  -3.750  -0.3013   0.03957   0.02931  -0.0463   0.7189   0.4400
  -3.500  -0.2720   0.03943   0.02924  -0.0462   0.7163   0.4690
  -3.250  -0.2898   0.04023   0.03011  -0.0402   0.7062   0.4830
  -3.000  -0.2720   0.04037   0.03030  -0.0385   0.7012   0.5096
  -2.750  -0.2454   0.04052   0.03052  -0.0376   0.6978   0.5365
  -2.500  -0.2299   0.04092   0.03096  -0.0356   0.6930   0.5601
  -2.250  -0.2328   0.04169   0.03177  -0.0316   0.6847   0.5790
  -2.000  -0.2120   0.04204   0.03213  -0.0300   0.6801   0.6026
  -1.750  -0.1846   0.04229   0.03235  -0.0291   0.6769   0.6262
  -1.500  -0.1829   0.04309   0.03314  -0.0257   0.6698   0.6446
  -1.250  -0.1739   0.04371   0.03375  -0.0231   0.6633   0.6641
  -1.000  -0.1518   0.04404   0.03403  -0.0218   0.6591   0.6847
  -0.750  -0.1235   0.04431   0.03424  -0.0209   0.6562   0.7039
  -0.500  -0.1287   0.04546   0.03543  -0.0168   0.6476   0.7179
  -0.250  -0.1147   0.04601   0.03594  -0.0147   0.6421   0.7353
   0.000  -0.0917   0.04627   0.03612  -0.0135   0.6383   0.7538
   0.250  -0.0630   0.04643   0.03621  -0.0127   0.6356   0.7714
   0.500  -0.0747   0.04781   0.03764  -0.0083   0.6257   0.7852
   0.750  -0.0565   0.04823   0.03801  -0.0067   0.6210   0.8019
   1.000  -0.0317   0.04840   0.03811  -0.0057   0.6176   0.8195
   1.500  -0.0141   0.05012   0.03981  -0.0016   0.6042   0.8498
   1.750   0.0111   0.05049   0.04012  -0.0012   0.6002   0.8653
   2.000   0.0425   0.05063   0.04019  -0.0015   0.5972   0.8808
   2.250   0.0454   0.05206   0.04163  -0.0001   0.5884   0.8957
   2.500   0.0750   0.05282   0.04236  -0.0015   0.5830   0.9081
   2.750   0.1134   0.05324   0.04272  -0.0036   0.5794   0.9204
   3.000   0.1575   0.05344   0.04285  -0.0064   0.5769   0.9321
   3.250   0.1660   0.05568   0.04512  -0.0077   0.5661   0.9435
   3.500   0.2081   0.05634   0.04574  -0.0113   0.5617   0.9531
   3.750   0.2565   0.05671   0.04606  -0.0152   0.5587   0.9620
   4.000   0.2727   0.05889   0.04827  -0.0177   0.5492   0.9721
   4.250   0.3099   0.05976   0.04912  -0.0211   0.5438   0.9818
   4.500   0.3542   0.06013   0.04946  -0.0247   0.5404   0.9917
   5.000   0.3459   0.06225   0.05153  -0.0205   0.5257   1.0000
   5.250   0.3550   0.06203   0.05123  -0.0181   0.5219   1.0000
   5.500   0.3728   0.06168   0.05079  -0.0165   0.5194   1.0000
   5.750   0.3412   0.06414   0.05322  -0.0124   0.5075   1.0000
   6.000   0.3610   0.06438   0.05339  -0.0117   0.5035   1.0000
   6.250   0.3886   0.06435   0.05329  -0.0115   0.5008   1.0000
   6.500   0.3700   0.06728   0.05621  -0.0096   0.4893   1.0000
   6.750   0.3934   0.06769   0.05657  -0.0095   0.4850   1.0000
   7.000   0.4230   0.06776   0.05658  -0.0096   0.4822   1.0000
   7.250   0.4077   0.07090   0.05974  -0.0083   0.4706   1.0000
   7.500   0.4316   0.07141   0.06022  -0.0083   0.4663   1.0000
   7.750   0.4623   0.07144   0.06020  -0.0084   0.4635   1.0000
   8.000   0.4469   0.07489   0.06369  -0.0075   0.4517   1.0000
   8.250   0.4716   0.07538   0.06416  -0.0075   0.4475   1.0000
   8.500   0.5030   0.07533   0.06408  -0.0076   0.4448   1.0000
   8.750   0.4863   0.07913   0.06791  -0.0069   0.4325   1.0000
   9.000   0.5119   0.07954   0.06833  -0.0070   0.4286   1.0000
   9.500   0.5249   0.08364   0.07246  -0.0066   0.4132   1.0000
   9.750   0.5522   0.08387   0.07269  -0.0066   0.4096   1.0000
  10.250   0.5629   0.08835   0.07723  -0.0065   0.3938   1.0000
  10.500   0.5920   0.08838   0.07726  -0.0064   0.3908   1.0000
  10.750   0.5772   0.09270   0.08165  -0.0066   0.3790   1.0000
  11.000   0.6005   0.09324   0.08221  -0.0065   0.3747   1.0000
  11.500   0.6110   0.09815   0.08719  -0.0069   0.3593   1.0000
  11.750   0.6374   0.09831   0.08737  -0.0067   0.3558   1.0000
  12.000   0.6255   0.10280   0.09192  -0.0074   0.3452   1.0000
  12.250   0.6450   0.10367   0.09284  -0.0074   0.3401   1.0000
  12.500   0.6736   0.10352   0.09271  -0.0072   0.3372   1.0000
  12.750   0.6546   0.10902   0.09828  -0.0082   0.3253   1.0000
  13.000   0.6787   0.10930   0.09860  -0.0081   0.3213   1.0000
  13.250   0.6699   0.11379   0.10315  -0.0091   0.3118   1.0000
  13.500   0.6849   0.11520   0.10461  -0.0093   0.3061   1.0000
  13.750   0.7120   0.11502   0.10446  -0.0091   0.3030   1.0000
  14.000   0.6942   0.12083   0.11034  -0.0107   0.2919   1.0000
  14.250   0.7158   0.12131   0.11087  -0.0106   0.2876   1.0000
  14.750   0.7218   0.12746   0.11713  -0.0124   0.2729   1.0000
  15.000   0.7477   0.12724   0.11695  -0.0121   0.2696   1.0000
  15.250   0.7314   0.13320   0.12297  -0.0142   0.2592   1.0000
  15.500   0.7514   0.13378   0.12360  -0.0142   0.2548   1.0000
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