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FX 83-W-108 (fx83w108-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 83-W-108 (fx83w108-il)
Reynolds number: 100,000
Max Cl/Cd: 60.41 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx83w108-il-100000-n5.txt
Download as CSV file: xf-fx83w108-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 83-W-108                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3862   0.09814   0.09307  -0.0472   1.0000   0.0367
  -9.250  -0.3966   0.09567   0.09068  -0.0457   1.0000   0.0365
  -9.000  -0.4079   0.09305   0.08815  -0.0445   0.9996   0.0363
  -8.750  -0.4003   0.08714   0.08225  -0.0505   0.9938   0.0362
  -8.500  -0.3977   0.08039   0.07551  -0.0574   0.9865   0.0364
  -8.250  -0.4013   0.07260   0.06774  -0.0655   0.9762   0.0365
  -8.000  -0.4091   0.05745   0.05240  -0.0853   0.9610   0.0361
  -7.750  -0.4061   0.04796   0.04237  -0.0971   0.9499   0.0361
  -7.500  -0.3897   0.04116   0.03484  -0.1041   0.9431   0.0368
  -7.250  -0.3722   0.03704   0.03012  -0.1065   0.9359   0.0372
  -7.000  -0.3473   0.03352   0.02591  -0.1089   0.9310   0.0379
  -6.750  -0.3176   0.03104   0.02320  -0.1110   0.9281   0.0390
  -6.500  -0.2941   0.02956   0.02151  -0.1114   0.9224   0.0403
  -6.250  -0.2665   0.02827   0.02000  -0.1123   0.9177   0.0430
  -6.000  -0.2345   0.02670   0.01804  -0.1137   0.9147   0.0458
  -5.750  -0.2012   0.02507   0.01617  -0.1153   0.9125   0.0479
  -5.500  -0.1795   0.02422   0.01528  -0.1147   0.9061   0.0506
  -5.250  -0.1498   0.02337   0.01430  -0.1154   0.9020   0.0547
  -5.000  -0.1169   0.02236   0.01312  -0.1166   0.8992   0.0586
  -4.750  -0.0833   0.02146   0.01222  -0.1181   0.8969   0.0640
  -4.500  -0.0625   0.02102   0.01167  -0.1170   0.8901   0.0696
  -4.250  -0.0335   0.02030   0.01095  -0.1175   0.8861   0.0761
  -4.000  -0.0009   0.01965   0.01024  -0.1187   0.8831   0.0874
  -3.750   0.0302   0.01904   0.00963  -0.1196   0.8800   0.1022
  -3.500   0.0515   0.01863   0.00929  -0.1187   0.8734   0.1265
  -3.250   0.0813   0.01795   0.00889  -0.1195   0.8697   0.1876
  -3.000   0.1138   0.01747   0.00869  -0.1207   0.8669   0.2712
  -2.750   0.1377   0.01743   0.00875  -0.1200   0.8615   0.3248
  -2.500   0.1638   0.01743   0.00876  -0.1197   0.8565   0.3651
  -2.250   0.1950   0.01736   0.00868  -0.1203   0.8531   0.4009
  -2.000   0.2284   0.01727   0.00859  -0.1213   0.8506   0.4374
  -1.750   0.2475   0.01740   0.00876  -0.1196   0.8437   0.4611
  -1.500   0.2758   0.01736   0.00870  -0.1196   0.8395   0.4845
  -1.250   0.3076   0.01724   0.00858  -0.1203   0.8365   0.5050
  -1.000   0.3336   0.01724   0.00860  -0.1198   0.8319   0.5233
  -0.750   0.3564   0.01730   0.00868  -0.1189   0.8260   0.5415
  -0.500   0.3871   0.01722   0.00862  -0.1193   0.8225   0.5633
  -0.250   0.4206   0.01708   0.00852  -0.1202   0.8198   0.5876
   0.000   0.4398   0.01725   0.00876  -0.1186   0.8130   0.6125
   0.250   0.4674   0.01720   0.00881  -0.1184   0.8085   0.6439
   0.500   0.4987   0.01702   0.00876  -0.1188   0.8053   0.6860
   0.750   0.5210   0.01700   0.00894  -0.1175   0.7998   0.7436
   1.000   0.5499   0.01678   0.00903  -0.1173   0.7946   0.8613
   1.250   0.5909   0.01669   0.00893  -0.1200   0.7910   1.0000
   1.500   0.6245   0.01672   0.00889  -0.1210   0.7877   1.0000
   1.750   0.6417   0.01714   0.00929  -0.1192   0.7797   1.0000
   2.000   0.6723   0.01723   0.00934  -0.1197   0.7755   1.0000
   2.250   0.7024   0.01733   0.00943  -0.1200   0.7712   1.0000
   2.500   0.7220   0.01769   0.00980  -0.1186   0.7637   1.0000
   2.750   0.7541   0.01770   0.00981  -0.1192   0.7592   1.0000
   3.000   0.7764   0.01797   0.01013  -0.1182   0.7520   1.0000
   3.250   0.8040   0.01807   0.01025  -0.1180   0.7456   1.0000
   3.500   0.8331   0.01809   0.01030  -0.1179   0.7390   1.0000
   3.750   0.8582   0.01813   0.01039  -0.1171   0.7297   1.0000
   4.000   0.8827   0.01815   0.01047  -0.1161   0.7194   1.0000
   4.250   0.9134   0.01790   0.01025  -0.1159   0.7088   1.0000
   4.500   0.9412   0.01766   0.01004  -0.1152   0.6950   1.0000
   4.750   0.9621   0.01760   0.01003  -0.1133   0.6779   1.0000
   5.000   0.9823   0.01758   0.01007  -0.1114   0.6595   1.0000
   5.250   1.0040   0.01757   0.01011  -0.1098   0.6403   1.0000
   5.500   1.0280   0.01751   0.01006  -0.1085   0.6193   1.0000
   5.750   1.0458   0.01762   0.01021  -0.1062   0.5917   1.0000
   6.000   1.0656   0.01771   0.01025  -0.1041   0.5565   1.0000
   6.250   1.0837   0.01794   0.01032  -0.1018   0.5094   1.0000
   6.500   1.0963   0.01850   0.01050  -0.0987   0.4411   1.0000
   6.750   1.0999   0.01949   0.01104  -0.0943   0.3661   1.0000
   7.000   1.0999   0.02072   0.01182  -0.0897   0.3009   1.0000
   7.250   1.1021   0.02201   0.01276  -0.0858   0.2461   1.0000
   7.500   1.1070   0.02327   0.01375  -0.0825   0.2023   1.0000
   7.750   1.1141   0.02448   0.01476  -0.0796   0.1684   1.0000
   8.000   1.1222   0.02569   0.01581  -0.0770   0.1418   1.0000
   8.250   1.1311   0.02689   0.01693  -0.0746   0.1227   1.0000
   8.500   1.1404   0.02810   0.01809  -0.0723   0.1084   1.0000
   8.750   1.1502   0.02931   0.01929  -0.0702   0.0974   1.0000
   9.000   1.1590   0.03062   0.02058  -0.0680   0.0884   1.0000
   9.250   1.1688   0.03191   0.02188  -0.0661   0.0809   1.0000
   9.500   1.1782   0.03327   0.02330  -0.0641   0.0750   1.0000
   9.750   1.1886   0.03459   0.02467  -0.0623   0.0695   1.0000
  10.000   1.1971   0.03611   0.02618  -0.0605   0.0652   1.0000
  10.250   1.2088   0.03745   0.02765  -0.0589   0.0610   1.0000
  10.500   1.2193   0.03887   0.02912  -0.0574   0.0575   1.0000
  10.750   1.2279   0.04058   0.03080  -0.0558   0.0548   1.0000
  11.000   1.2412   0.04199   0.03241  -0.0545   0.0519   1.0000
  11.250   1.2540   0.04355   0.03409  -0.0531   0.0494   1.0000
  11.500   1.2659   0.04515   0.03578  -0.0519   0.0474   1.0000
  11.750   1.2768   0.04685   0.03751  -0.0507   0.0455   1.0000
  12.000   1.2894   0.04869   0.03945  -0.0495   0.0436   1.0000
  12.250   1.3014   0.05052   0.04152  -0.0484   0.0419   1.0000
  12.500   1.3117   0.05250   0.04372  -0.0472   0.0402   1.0000
  12.750   1.3217   0.05458   0.04597  -0.0461   0.0390   1.0000
  13.000   1.3297   0.05677   0.04830  -0.0450   0.0379   1.0000
  13.250   1.3371   0.05906   0.05072  -0.0440   0.0371   1.0000
  13.500   1.3442   0.06152   0.05326  -0.0430   0.0362   1.0000
  13.750   1.3461   0.06457   0.05653  -0.0420   0.0354   1.0000
  14.000   1.3414   0.06797   0.06028  -0.0410   0.0347   1.0000
  14.250   1.3340   0.07173   0.06436  -0.0402   0.0341   1.0000
  14.500   1.3246   0.07574   0.06867  -0.0398   0.0335   1.0000
  14.750   1.3125   0.08023   0.07344  -0.0397   0.0330   1.0000
  15.000   1.2981   0.08511   0.07860  -0.0402   0.0326   1.0000
  15.250   1.2814   0.09060   0.08437  -0.0413   0.0324   1.0000
  15.500   1.2613   0.09692   0.09095  -0.0432   0.0322   1.0000
  15.750   1.2380   0.10419   0.09849  -0.0462   0.0322   1.0000
  16.000   1.2105   0.11288   0.10745  -0.0507   0.0323   1.0000
  16.250   1.1753   0.12423   0.11906  -0.0577   0.0326   1.0000
  16.500   1.1245   0.14163   0.13671  -0.0694   0.0334   1.0000
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