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FX 84-W-175 (fx84w175-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 84-W-175 (fx84w175-il)
Reynolds number: 100,000
Max Cl/Cd: 34.13 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx84w175-il-100000-n5.txt
Download as CSV file: xf-fx84w175-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 84-W-175                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.1821   0.09801   0.09243  -0.1041   0.9281   0.0496
 -12.000  -0.1836   0.09331   0.08772  -0.1068   0.9211   0.0505
 -11.500  -0.4029   0.05099   0.04465  -0.1341   0.8977   0.0487
 -11.250  -0.4125   0.04861   0.04213  -0.1338   0.8891   0.0492
 -11.000  -0.4235   0.04630   0.03963  -0.1328   0.8804   0.0498
 -10.750  -0.4329   0.04448   0.03762  -0.1307   0.8723   0.0504
 -10.500  -0.4429   0.04282   0.03574  -0.1278   0.8642   0.0511
 -10.250  -0.4464   0.04087   0.03349  -0.1255   0.8585   0.0520
 -10.000  -0.4490   0.03913   0.03146  -0.1230   0.8505   0.0529
  -9.750  -0.4469   0.03715   0.02904  -0.1208   0.8448   0.0541
  -9.500  -0.4331   0.03599   0.02778  -0.1196   0.8405   0.0554
  -9.250  -0.4207   0.03529   0.02703  -0.1181   0.8337   0.0567
  -9.000  -0.4060   0.03427   0.02585  -0.1168   0.8287   0.0585
  -8.750  -0.3898   0.03295   0.02423  -0.1157   0.8250   0.0606
  -8.500  -0.3757   0.03185   0.02289  -0.1141   0.8191   0.0623
  -8.250  -0.3577   0.03117   0.02222  -0.1132   0.8138   0.0640
  -8.000  -0.3376   0.03042   0.02137  -0.1123   0.8098   0.0665
  -7.750  -0.3156   0.02944   0.02013  -0.1116   0.8067   0.0697
  -7.500  -0.2994   0.02884   0.01950  -0.1103   0.8003   0.0719
  -7.250  -0.2798   0.02827   0.01892  -0.1093   0.7954   0.0746
  -7.000  -0.2570   0.02757   0.01806  -0.1087   0.7918   0.0785
  -6.750  -0.2329   0.02680   0.01723  -0.1082   0.7889   0.0822
  -6.500  -0.2169   0.02651   0.01694  -0.1067   0.7824   0.0858
  -6.250  -0.1957   0.02603   0.01631  -0.1058   0.7777   0.0908
  -6.000  -0.1727   0.02543   0.01575  -0.1052   0.7742   0.0956
  -5.750  -0.1470   0.02486   0.01507  -0.1049   0.7715   0.1022
  -5.500  -0.1318   0.02464   0.01491  -0.1032   0.7650   0.1074
  -5.250  -0.1106   0.02430   0.01451  -0.1023   0.7602   0.1150
  -5.000  -0.0867   0.02380   0.01404  -0.1018   0.7568   0.1235
  -4.750  -0.0605   0.02329   0.01349  -0.1015   0.7542   0.1340
  -4.500  -0.0449   0.02323   0.01345  -0.0998   0.7478   0.1443
  -4.250  -0.0243   0.02294   0.01321  -0.0989   0.7429   0.1569
  -4.000   0.0006   0.02253   0.01282  -0.0985   0.7397   0.1735
  -3.750   0.0276   0.02207   0.01238  -0.0984   0.7371   0.1949
  -3.500   0.0429   0.02204   0.01246  -0.0967   0.7308   0.2160
  -3.250   0.0630   0.02179   0.01233  -0.0956   0.7259   0.2458
  -3.000   0.0878   0.02135   0.01203  -0.0953   0.7226   0.2883
  -2.750   0.1138   0.02078   0.01171  -0.0951   0.7201   0.3488
  -2.500   0.1273   0.02071   0.01194  -0.0930   0.7139   0.4153
  -2.250   0.1448   0.02051   0.01209  -0.0912   0.7088   0.4974
  -2.000   0.1686   0.02029   0.01212  -0.0900   0.7056   0.5768
  -1.750   0.1957   0.02015   0.01207  -0.0892   0.7031   0.6367
  -1.500   0.2100   0.02050   0.01250  -0.0867   0.6972   0.6748
  -1.250   0.2278   0.02074   0.01277  -0.0847   0.6918   0.7068
  -1.000   0.2531   0.02077   0.01276  -0.0836   0.6886   0.7357
  -0.750   0.2810   0.02073   0.01266  -0.0829   0.6862   0.7611
  -0.500   0.2929   0.02117   0.01311  -0.0801   0.6800   0.7820
  -0.250   0.3091   0.02143   0.01336  -0.0778   0.6746   0.8020
   0.000   0.3340   0.02143   0.01330  -0.0767   0.6715   0.8217
   0.250   0.3615   0.02135   0.01315  -0.0759   0.6691   0.8414
   0.500   0.3662   0.02190   0.01375  -0.0718   0.6620   0.8607
   0.750   0.3824   0.02210   0.01393  -0.0693   0.6571   0.8807
   1.000   0.4107   0.02201   0.01379  -0.0688   0.6542   0.8982
   1.250   0.4443   0.02183   0.01352  -0.0695   0.6520   0.9113
   1.500   0.4526   0.02247   0.01420  -0.0669   0.6444   0.9270
   1.750   0.4854   0.02257   0.01426  -0.0680   0.6401   0.9376
   2.000   0.5259   0.02247   0.01408  -0.0704   0.6374   0.9463
   2.250   0.5692   0.02227   0.01381  -0.0732   0.6353   0.9543
   2.500   0.5944   0.02291   0.01447  -0.0741   0.6285   0.9664
   2.750   0.6316   0.02312   0.01466  -0.0765   0.6238   0.9755
   3.000   0.6749   0.02302   0.01451  -0.0796   0.6208   0.9829
   3.250   0.7225   0.02279   0.01422  -0.0833   0.6185   0.9881
   3.500   0.7213   0.02365   0.01513  -0.0800   0.6105   1.0000
   3.750   0.7240   0.02383   0.01527  -0.0762   0.6053   1.0000
   4.000   0.7546   0.02364   0.01503  -0.0767   0.6026   1.0000
   4.250   0.7886   0.02345   0.01477  -0.0777   0.6001   1.0000
   4.500   0.7583   0.02502   0.01638  -0.0699   0.5892   1.0000
   4.750   0.7922   0.02484   0.01617  -0.0708   0.5865   1.0000
   5.000   0.8325   0.02450   0.01579  -0.0727   0.5844   1.0000
   5.500   0.8413   0.02630   0.01761  -0.0672   0.5703   1.0000
   5.750   0.8806   0.02590   0.01720  -0.0687   0.5682   1.0000
   6.250   0.8924   0.02794   0.01928  -0.0641   0.5540   1.0000
   6.500   0.9314   0.02746   0.01880  -0.0654   0.5517   1.0000
   7.000   0.9440   0.02967   0.02109  -0.0613   0.5373   1.0000
   7.250   0.9837   0.02907   0.02051  -0.0625   0.5351   1.0000
   7.750   0.9973   0.03134   0.02287  -0.0587   0.5203   1.0000
   8.000   1.0400   0.03047   0.02201  -0.0600   0.5180   1.0000
   8.250   1.0157   0.03353   0.02515  -0.0556   0.5058   1.0000
   8.500   1.0537   0.03279   0.02444  -0.0564   0.5029   1.0000
   9.000   1.0710   0.03508   0.02684  -0.0534   0.4879   1.0000
   9.250   1.1140   0.03394   0.02575  -0.0545   0.4852   1.0000
   9.500   1.0917   0.03725   0.02915  -0.0509   0.4730   1.0000
   9.750   1.1312   0.03622   0.02815  -0.0516   0.4697   1.0000
  10.250   1.1508   0.03844   0.03051  -0.0490   0.4540   1.0000
  10.750   1.1726   0.04055   0.03276  -0.0468   0.4381   1.0000
  11.000   1.1730   0.04251   0.03480  -0.0452   0.4286   1.0000
  11.250   1.1979   0.04237   0.03471  -0.0448   0.4214   1.0000
  11.500   1.1947   0.04464   0.03706  -0.0432   0.4105   1.0000
  11.750   1.2322   0.04322   0.03564  -0.0432   0.4028   1.0000
  12.000   1.2205   0.04630   0.03881  -0.0414   0.3899   1.0000
  12.250   1.2238   0.04810   0.04068  -0.0402   0.3782   1.0000
  12.500   1.2410   0.04853   0.04112  -0.0395   0.3671   1.0000
  12.750   1.2503   0.04978   0.04239  -0.0386   0.3548   1.0000
  13.000   1.2473   0.05242   0.04510  -0.0376   0.3417   1.0000
  13.250   1.2508   0.05444   0.04717  -0.0368   0.3288   1.0000
  13.500   1.2565   0.05624   0.04899  -0.0361   0.3156   1.0000
  13.750   1.2623   0.05807   0.05082  -0.0354   0.3021   1.0000
  14.000   1.2667   0.06008   0.05283  -0.0348   0.2881   1.0000
  14.250   1.2693   0.06236   0.05510  -0.0343   0.2736   1.0000
  14.500   1.2700   0.06493   0.05765  -0.0338   0.2589   1.0000
  14.750   1.2693   0.06777   0.06050  -0.0335   0.2441   1.0000
  15.000   1.2680   0.07075   0.06347  -0.0333   0.2295   1.0000
  15.250   1.2657   0.07390   0.06661  -0.0332   0.2148   1.0000
  15.500   1.2631   0.07720   0.06990  -0.0332   0.2005   1.0000
  15.750   1.2598   0.08066   0.07335  -0.0334   0.1865   1.0000
  16.000   1.2558   0.08430   0.07697  -0.0338   0.1730   1.0000
  16.250   1.2517   0.08801   0.08068  -0.0342   0.1601   1.0000
  16.500   1.2476   0.09182   0.08447  -0.0348   0.1479   1.0000
  16.750   1.2434   0.09568   0.08833  -0.0354   0.1370   1.0000
  17.000   1.2389   0.09966   0.09226  -0.0363   0.1269   1.0000
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