Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

FX 83-W-108 (fx83w108-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: FX 83-W-108 (fx83w108-il)
Reynolds number: 1,000,000
Max Cl/Cd: 115.38 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx83w108-il-1000000-n5.txt
Download as CSV file: xf-fx83w108-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.8216   0.06056   0.05815  -0.0757   1.0000   0.0099
 -13.750  -0.8744   0.05027   0.04774  -0.0811   1.0000   0.0099
 -13.500  -0.8889   0.04108   0.03837  -0.0922   0.9971   0.0099
 -13.250  -0.8893   0.03005   0.02699  -0.1116   0.9877   0.0099
 -13.000  -0.8715   0.02720   0.02396  -0.1159   0.9816   0.0100
 -12.750  -0.8505   0.02520   0.02181  -0.1186   0.9766   0.0101
 -12.500  -0.8286   0.02364   0.02012  -0.1203   0.9701   0.0102
 -12.250  -0.8037   0.02233   0.01868  -0.1220   0.9641   0.0104
 -12.000  -0.7755   0.02097   0.01718  -0.1242   0.9582   0.0105
 -11.750  -0.7435   0.01986   0.01595  -0.1267   0.9532   0.0107
 -11.500  -0.7097   0.01871   0.01466  -0.1296   0.9471   0.0108
 -11.250  -0.6712   0.01770   0.01351  -0.1332   0.9424   0.0111
 -11.000  -0.6353   0.01677   0.01244  -0.1361   0.9347   0.0112
 -10.750  -0.5990   0.01600   0.01154  -0.1389   0.9269   0.0115
 -10.500  -0.5682   0.01529   0.01070  -0.1403   0.9161   0.0116
 -10.250  -0.5392   0.01472   0.00998  -0.1413   0.9056   0.0118
 -10.000  -0.5119   0.01425   0.00939  -0.1417   0.8957   0.0120
  -9.750  -0.4877   0.01369   0.00872  -0.1415   0.8859   0.0122
  -9.500  -0.4637   0.01310   0.00803  -0.1413   0.8773   0.0126
  -9.250  -0.4393   0.01266   0.00751  -0.1410   0.8687   0.0130
  -9.000  -0.4145   0.01230   0.00707  -0.1406   0.8611   0.0133
  -8.750  -0.3897   0.01195   0.00664  -0.1403   0.8532   0.0136
  -8.500  -0.3647   0.01163   0.00624  -0.1399   0.8465   0.0139
  -8.250  -0.3394   0.01133   0.00587  -0.1396   0.8397   0.0143
  -8.000  -0.3141   0.01103   0.00549  -0.1392   0.8338   0.0147
  -7.750  -0.2885   0.01074   0.00513  -0.1389   0.8279   0.0150
  -7.500  -0.2628   0.01050   0.00482  -0.1386   0.8218   0.0154
  -7.250  -0.2373   0.01019   0.00445  -0.1382   0.8165   0.0161
  -7.000  -0.2113   0.00994   0.00417  -0.1380   0.8111   0.0170
  -6.750  -0.1853   0.00973   0.00391  -0.1377   0.8059   0.0178
  -6.500  -0.1589   0.00954   0.00368  -0.1374   0.8011   0.0187
  -6.250  -0.1323   0.00936   0.00345  -0.1372   0.7962   0.0195
  -6.000  -0.1061   0.00914   0.00321  -0.1369   0.7913   0.0212
  -5.750  -0.0795   0.00898   0.00302  -0.1367   0.7868   0.0228
  -5.500  -0.0525   0.00884   0.00285  -0.1365   0.7822   0.0242
  -5.250  -0.0259   0.00866   0.00265  -0.1363   0.7775   0.0259
  -4.750   0.0278   0.00838   0.00233  -0.1358   0.7691   0.0297
  -4.500   0.0548   0.00826   0.00217  -0.1356   0.7649   0.0315
  -4.250   0.0816   0.00812   0.00203  -0.1354   0.7607   0.0349
  -4.000   0.1085   0.00802   0.00191  -0.1352   0.7568   0.0379
  -3.750   0.1357   0.00787   0.00179  -0.1350   0.7530   0.0438
  -3.500   0.1628   0.00776   0.00167  -0.1349   0.7490   0.0501
  -3.250   0.1898   0.00765   0.00157  -0.1346   0.7450   0.0575
  -3.000   0.2166   0.00754   0.00147  -0.1344   0.7413   0.0692
  -2.750   0.2437   0.00739   0.00138  -0.1343   0.7377   0.0865
  -2.500   0.2705   0.00722   0.00129  -0.1340   0.7336   0.1127
  -2.250   0.2968   0.00703   0.00121  -0.1338   0.7296   0.1513
  -2.000   0.3232   0.00688   0.00115  -0.1335   0.7260   0.1879
  -1.750   0.3501   0.00673   0.00111  -0.1333   0.7221   0.2210
  -1.500   0.3768   0.00662   0.00108  -0.1330   0.7175   0.2530
  -1.250   0.4030   0.00651   0.00106  -0.1327   0.7128   0.2901
  -1.000   0.4300   0.00646   0.00106  -0.1325   0.7089   0.3147
  -0.750   0.4572   0.00640   0.00107  -0.1323   0.7049   0.3398
  -0.500   0.4842   0.00637   0.00108  -0.1321   0.7009   0.3599
  -0.250   0.5111   0.00636   0.00109  -0.1318   0.6968   0.3768
   0.000   0.5383   0.00635   0.00111  -0.1316   0.6931   0.3908
   0.250   0.5655   0.00633   0.00113  -0.1314   0.6887   0.4021
   0.500   0.5924   0.00635   0.00115  -0.1311   0.6835   0.4103
   0.750   0.6191   0.00636   0.00117  -0.1308   0.6782   0.4213
   1.000   0.6459   0.00636   0.00121  -0.1305   0.6712   0.4313
   1.250   0.6717   0.00640   0.00123  -0.1300   0.6621   0.4414
   1.500   0.6968   0.00645   0.00127  -0.1293   0.6490   0.4527
   1.750   0.7219   0.00649   0.00132  -0.1286   0.6358   0.4662
   2.000   0.7460   0.00658   0.00138  -0.1278   0.6177   0.4799
   2.250   0.7681   0.00674   0.00145  -0.1265   0.5879   0.4938
   2.500   0.7913   0.00687   0.00155  -0.1255   0.5638   0.5103
   2.750   0.8134   0.00705   0.00167  -0.1242   0.5366   0.5308
   3.000   0.8353   0.00724   0.00181  -0.1230   0.5097   0.5530
   3.250   0.8515   0.00769   0.00206  -0.1207   0.4508   0.5818
   3.500   0.8662   0.00820   0.00237  -0.1181   0.3849   0.6198
   3.750   0.8824   0.00858   0.00266  -0.1159   0.3360   0.6704
   4.000   0.8978   0.00893   0.00296  -0.1134   0.2899   0.7319
   4.250   0.9117   0.00914   0.00325  -0.1105   0.2537   0.8216
   4.500   0.9616   0.00957   0.00370  -0.1160   0.2009   1.0000
   4.750   0.9813   0.01000   0.00398  -0.1145   0.1708   1.0000
   5.000   1.0013   0.01041   0.00425  -0.1131   0.1452   1.0000
   5.250   1.0221   0.01076   0.00452  -0.1118   0.1256   1.0000
   5.500   1.0410   0.01122   0.00484  -0.1102   0.1012   1.0000
   5.750   1.0614   0.01158   0.00512  -0.1088   0.0862   1.0000
   6.000   1.0821   0.01192   0.00540  -0.1075   0.0759   1.0000
   6.250   1.1014   0.01227   0.00570  -0.1059   0.0652   1.0000
   6.500   1.1207   0.01261   0.00600  -0.1043   0.0575   1.0000
   6.750   1.1404   0.01295   0.00630  -0.1028   0.0506   1.0000
   7.000   1.1597   0.01332   0.00664  -0.1013   0.0447   1.0000
   7.250   1.1800   0.01365   0.00696  -0.1000   0.0409   1.0000
   7.500   1.1992   0.01404   0.00732  -0.0986   0.0363   1.0000
   7.750   1.2192   0.01439   0.00768  -0.0973   0.0340   1.0000
   8.000   1.2388   0.01478   0.00807  -0.0959   0.0317   1.0000
   8.250   1.2577   0.01521   0.00849  -0.0945   0.0294   1.0000
   8.500   1.2775   0.01561   0.00891  -0.0933   0.0278   1.0000
   8.750   1.2970   0.01601   0.00934  -0.0920   0.0266   1.0000
   9.000   1.3156   0.01648   0.00981  -0.0907   0.0247   1.0000
   9.250   1.3334   0.01701   0.01034  -0.0893   0.0230   1.0000
   9.500   1.3519   0.01749   0.01085  -0.0880   0.0219   1.0000
   9.750   1.3702   0.01800   0.01139  -0.0867   0.0209   1.0000
  10.000   1.3876   0.01856   0.01197  -0.0854   0.0196   1.0000
  10.250   1.4043   0.01919   0.01261  -0.0839   0.0184   1.0000
  10.500   1.4205   0.01986   0.01330  -0.0825   0.0176   1.0000
  10.750   1.4374   0.02048   0.01397  -0.0812   0.0171   1.0000
  11.000   1.4536   0.02117   0.01470  -0.0799   0.0164   1.0000
  11.250   1.4689   0.02192   0.01549  -0.0785   0.0159   1.0000
  11.500   1.4838   0.02271   0.01630  -0.0771   0.0153   1.0000
  11.750   1.4981   0.02355   0.01719  -0.0757   0.0148   1.0000
  12.000   1.5108   0.02452   0.01819  -0.0742   0.0141   1.0000
  12.250   1.5236   0.02550   0.01921  -0.0727   0.0137   1.0000
  12.500   1.5374   0.02641   0.02019  -0.0714   0.0135   1.0000
  12.750   1.5514   0.02730   0.02113  -0.0702   0.0129   1.0000
  13.000   1.5629   0.02841   0.02230  -0.0687   0.0128   1.0000
  13.250   1.5753   0.02945   0.02338  -0.0675   0.0123   1.0000
  13.500   1.5862   0.03063   0.02463  -0.0661   0.0120   1.0000
  13.750   1.5962   0.03189   0.02594  -0.0647   0.0117   1.0000
  14.000   1.6058   0.03320   0.02729  -0.0634   0.0113   1.0000
  14.250   1.6137   0.03467   0.02883  -0.0620   0.0110   1.0000
  14.500   1.6203   0.03630   0.03052  -0.0606   0.0107   1.0000
  14.750   1.6273   0.03789   0.03219  -0.0593   0.0105   1.0000
  15.000   1.6353   0.03943   0.03381  -0.0581   0.0104   1.0000
  15.250   1.6419   0.04113   0.03558  -0.0570   0.0103   1.0000
  15.500   1.6494   0.04279   0.03732  -0.0560   0.0101   1.0000
  15.750   1.6556   0.04460   0.03922  -0.0550   0.0099   1.0000
  16.000   1.6608   0.04653   0.04123  -0.0540   0.0097   1.0000
  16.250   1.6648   0.04863   0.04342  -0.0531   0.0095   1.0000
  16.500   1.6690   0.05077   0.04564  -0.0524   0.0094   1.0000
  16.750   1.6721   0.05308   0.04804  -0.0517   0.0092   1.0000
  17.000   1.6756   0.05538   0.05040  -0.0511   0.0089   1.0000
  17.250   1.6762   0.05805   0.05316  -0.0506   0.0088   1.0000
  17.500   1.6765   0.06083   0.05603  -0.0502   0.0086   1.0000
  17.750   1.6757   0.06381   0.05908  -0.0499   0.0084   1.0000
  18.000   1.6731   0.06709   0.06244  -0.0498   0.0081   1.0000
  18.250   1.6685   0.07071   0.06617  -0.0499   0.0080   1.0000
  18.500   1.6653   0.07419   0.06975  -0.0501   0.0079   1.0000
  18.750   1.6605   0.07798   0.07366  -0.0505   0.0078   1.0000
  19.000   1.6548   0.08198   0.07777  -0.0510   0.0077   1.0000
  19.250   1.6488   0.08613   0.08203  -0.0518   0.0076   1.0000
<< Back to FX 83-W-108 (fx83w108-il)

Polar data table (+)

Polar graphs


<< Back to FX 83-W-108 (fx83w108-il)