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FX 68-H-120 (fx68h120-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 68-H-120 (fx68h120-il)
Reynolds number: 200,000
Max Cl/Cd: 54.26 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx68h120-il-200000-n5.txt
Download as CSV file: xf-fx68h120-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 68-H-120                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.5683   0.09147   0.08815  -0.0230   1.0000   0.0111
 -11.750  -0.5922   0.08226   0.07894  -0.0284   1.0000   0.0106
 -11.500  -0.6279   0.07036   0.06698  -0.0364   1.0000   0.0101
 -11.250  -0.6559   0.05892   0.05539  -0.0463   1.0000   0.0098
 -11.000  -0.6774   0.04990   0.04615  -0.0561   1.0000   0.0097
 -10.750  -0.6945   0.04494   0.04095  -0.0597   1.0000   0.0097
 -10.500  -0.7062   0.04154   0.03732  -0.0599   0.9892   0.0097
 -10.250  -0.7045   0.03832   0.03374  -0.0608   0.9687   0.0100
 -10.000  -0.6980   0.03572   0.03079  -0.0606   0.9586   0.0104
  -9.750  -0.6882   0.03409   0.02884  -0.0595   0.9497   0.0109
  -9.500  -0.6788   0.03222   0.02665  -0.0580   0.9424   0.0111
  -9.250  -0.6720   0.02984   0.02400  -0.0560   0.9353   0.0116
  -9.000  -0.6602   0.02807   0.02201  -0.0543   0.9302   0.0118
  -8.750  -0.6456   0.02654   0.02031  -0.0529   0.9249   0.0122
  -8.500  -0.6298   0.02526   0.01885  -0.0513   0.9200   0.0125
  -8.250  -0.6126   0.02414   0.01758  -0.0499   0.9158   0.0130
  -8.000  -0.5937   0.02304   0.01634  -0.0487   0.9114   0.0136
  -7.750  -0.5745   0.02207   0.01518  -0.0474   0.9076   0.0142
  -7.500  -0.5552   0.02118   0.01413  -0.0460   0.9042   0.0149
  -7.250  -0.5339   0.02037   0.01317  -0.0450   0.9003   0.0158
  -7.000  -0.5122   0.01964   0.01231  -0.0441   0.8964   0.0169
  -6.750  -0.4917   0.01877   0.01134  -0.0429   0.8931   0.0190
  -6.500  -0.4693   0.01816   0.01060  -0.0419   0.8903   0.0213
  -6.250  -0.4454   0.01757   0.00986  -0.0412   0.8869   0.0239
  -6.000  -0.4224   0.01680   0.00905  -0.0404   0.8831   0.0304
  -5.750  -0.3992   0.01610   0.00835  -0.0396   0.8801   0.0456
  -5.500  -0.3765   0.01546   0.00791  -0.0388   0.8773   0.0808
  -5.250  -0.3513   0.01522   0.00771  -0.0383   0.8747   0.1079
  -5.000  -0.3246   0.01511   0.00763  -0.0382   0.8711   0.1276
  -4.750  -0.2981   0.01504   0.00753  -0.0379   0.8679   0.1428
  -4.500  -0.2723   0.01490   0.00734  -0.0374   0.8649   0.1533
  -4.250  -0.2466   0.01475   0.00708  -0.0369   0.8624   0.1616
  -4.000  -0.2216   0.01452   0.00684  -0.0362   0.8567   0.1687
  -3.750  -0.1978   0.01426   0.00650  -0.0350   0.8496   0.1754
  -3.500  -0.1742   0.01397   0.00617  -0.0338   0.8406   0.1815
  -3.250  -0.1504   0.01368   0.00583  -0.0325   0.8338   0.1888
  -3.000  -0.1252   0.01344   0.00557  -0.0319   0.8258   0.1958
  -2.750  -0.1001   0.01320   0.00530  -0.0311   0.8206   0.2043
  -2.500  -0.0745   0.01298   0.00511  -0.0305   0.8143   0.2150
  -2.250  -0.0492   0.01275   0.00489  -0.0298   0.8081   0.2276
  -2.000  -0.0238   0.01252   0.00468  -0.0291   0.8017   0.2434
  -1.750   0.0013   0.01226   0.00448  -0.0284   0.7941   0.2656
  -1.500   0.0261   0.01197   0.00431  -0.0277   0.7863   0.2992
  -1.250   0.0501   0.01161   0.00413  -0.0268   0.7782   0.3496
  -1.000   0.0732   0.01123   0.00399  -0.0258   0.7682   0.4179
  -0.750   0.0952   0.01078   0.00384  -0.0244   0.7571   0.5015
  -0.500   0.1156   0.01028   0.00371  -0.0226   0.7445   0.6051
   0.000   0.2074   0.00948   0.00368  -0.0284   0.7041   0.8798
   0.250   0.2529   0.00951   0.00358  -0.0314   0.6695   0.9170
   0.500   0.2866   0.00963   0.00343  -0.0321   0.6182   0.9399
   0.750   0.3165   0.00997   0.00335  -0.0323   0.5514   0.9568
   1.000   0.3495   0.01040   0.00343  -0.0333   0.4987   0.9695
   1.250   0.3878   0.01077   0.00352  -0.0357   0.4569   0.9790
   1.500   0.4442   0.01115   0.00364  -0.0419   0.4187   0.9958
   1.750   0.4792   0.01139   0.00371  -0.0437   0.3926   1.0000
   2.000   0.5023   0.01161   0.00380  -0.0429   0.3716   1.0000
   2.250   0.5251   0.01185   0.00390  -0.0421   0.3519   1.0000
   2.500   0.5480   0.01208   0.00402  -0.0414   0.3346   1.0000
   2.750   0.5708   0.01231   0.00416  -0.0406   0.3190   1.0000
   3.000   0.5935   0.01254   0.00431  -0.0397   0.3050   1.0000
   3.250   0.6161   0.01278   0.00447  -0.0389   0.2922   1.0000
   3.750   0.6610   0.01328   0.00486  -0.0371   0.2684   1.0000
   4.000   0.6833   0.01354   0.00507  -0.0362   0.2576   1.0000
   4.250   0.7053   0.01382   0.00529  -0.0352   0.2474   1.0000
   4.500   0.7269   0.01412   0.00553  -0.0342   0.2381   1.0000
   4.750   0.7490   0.01438   0.00580  -0.0332   0.2300   1.0000
   5.000   0.7702   0.01471   0.00608  -0.0322   0.2232   1.0000
   5.250   0.7921   0.01498   0.00637  -0.0312   0.2167   1.0000
   5.500   0.8131   0.01532   0.00667  -0.0301   0.2110   1.0000
   5.750   0.8345   0.01563   0.00702  -0.0290   0.2060   1.0000
   6.000   0.8557   0.01595   0.00736  -0.0279   0.2012   1.0000
   6.250   0.8761   0.01632   0.00772  -0.0267   0.1970   1.0000
   6.500   0.8970   0.01666   0.00809  -0.0255   0.1922   1.0000
   6.750   0.9172   0.01699   0.00841  -0.0244   0.1842   1.0000
   7.000   0.9375   0.01729   0.00872  -0.0232   0.1737   1.0000
   7.250   0.9572   0.01764   0.00906  -0.0220   0.1625   1.0000
   7.500   0.9761   0.01803   0.00942  -0.0207   0.1535   1.0000
   7.750   0.9954   0.01841   0.00977  -0.0194   0.1391   1.0000
   8.000   1.0137   0.01888   0.01017  -0.0180   0.1189   1.0000
   8.500   1.0232   0.02203   0.01262  -0.0120   0.0145   1.0000
   8.750   1.0375   0.02275   0.01344  -0.0099   0.0127   1.0000
   9.000   1.0508   0.02345   0.01428  -0.0078   0.0118   1.0000
   9.250   1.0615   0.02420   0.01519  -0.0053   0.0112   1.0000
   9.500   1.0707   0.02506   0.01620  -0.0027   0.0106   1.0000
   9.750   1.0799   0.02598   0.01726  -0.0004   0.0102   1.0000
  10.000   1.0869   0.02711   0.01855   0.0020   0.0097   1.0000
  10.250   1.0917   0.02843   0.02004   0.0044   0.0092   1.0000
  10.500   1.0925   0.03008   0.02187   0.0069   0.0084   1.0000
  10.750   1.0976   0.03145   0.02339   0.0087   0.0082   1.0000
  11.000   1.1002   0.03307   0.02516   0.0106   0.0079   1.0000
  11.250   1.1005   0.03494   0.02718   0.0123   0.0077   1.0000
  11.500   1.0990   0.03706   0.02945   0.0137   0.0076   1.0000
  11.750   1.0952   0.03954   0.03208   0.0148   0.0076   1.0000
  12.000   1.0885   0.04251   0.03520   0.0154   0.0073   1.0000
  12.250   1.0817   0.04577   0.03860   0.0156   0.0073   1.0000
  12.500   1.0722   0.04968   0.04269   0.0150   0.0072   1.0000
  12.750   1.0622   0.05408   0.04723   0.0138   0.0071   1.0000
  13.000   1.0509   0.05910   0.05239   0.0119   0.0071   1.0000
  13.250   1.0414   0.06415   0.05758   0.0098   0.0071   1.0000
  13.500   1.0308   0.06951   0.06306   0.0076   0.0072   1.0000
  13.750   1.0200   0.07493   0.06858   0.0054   0.0070   1.0000
  14.000   1.0118   0.07992   0.07366   0.0034   0.0069   1.0000
  14.250   1.0052   0.08455   0.07836   0.0017   0.0070   1.0000
  14.500   1.0001   0.08883   0.08270   0.0003   0.0068   1.0000
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