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FX 83-W-108 (fx83w108-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 83-W-108 (fx83w108-il)
Reynolds number: 200,000
Max Cl/Cd: 90.49 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx83w108-il-200000.txt
Download as CSV file: xf-fx83w108-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3746   0.11248   0.10889  -0.0481   1.0000   0.0577
 -10.000  -0.3874   0.11020   0.10669  -0.0477   1.0000   0.0579
  -9.750  -0.4018   0.10852   0.10509  -0.0458   1.0000   0.0579
  -9.500  -0.4190   0.10704   0.10369  -0.0433   1.0000   0.0580
  -9.250  -0.4113   0.10302   0.09969  -0.0389   1.0000   0.0593
  -9.000  -0.4023   0.10150   0.09817  -0.0368   0.9993   0.0606
  -8.750  -0.3820   0.09834   0.09500  -0.0397   0.9967   0.0631
  -8.500  -0.3682   0.09403   0.09069  -0.0449   0.9927   0.0662
  -8.250  -0.3776   0.08572   0.08241  -0.0644   0.9811   0.0702
  -8.000  -0.3699   0.07914   0.07585  -0.0682   0.9760   0.0715
  -7.750  -0.3488   0.07710   0.07379  -0.0672   0.9726   0.0727
  -7.500  -0.3252   0.07424   0.07091  -0.0697   0.9695   0.0748
  -7.250  -0.3105   0.06996   0.06662  -0.0753   0.9616   0.0775
  -7.000  -0.3254   0.03685   0.03157  -0.1131   0.9438   0.0473
  -6.750  -0.2947   0.03217   0.02652  -0.1165   0.9419   0.0461
  -6.500  -0.2778   0.02999   0.02395  -0.1158   0.9339   0.0465
  -6.250  -0.2474   0.02694   0.02038  -0.1179   0.9308   0.0476
  -6.000  -0.2135   0.02423   0.01742  -0.1202   0.9290   0.0491
  -5.750  -0.1762   0.02255   0.01554  -0.1225   0.9276   0.0510
  -5.500  -0.1569   0.02166   0.01450  -0.1211   0.9204   0.0528
  -5.250  -0.1234   0.02067   0.01331  -0.1223   0.9174   0.0561
  -5.000  -0.0875   0.01924   0.01175  -0.1242   0.9154   0.0605
  -4.750  -0.0491   0.01827   0.01076  -0.1264   0.9138   0.0656
  -4.500  -0.0111   0.01733   0.00974  -0.1285   0.9123   0.0725
  -4.250   0.0053   0.01695   0.00940  -0.1265   0.9045   0.0778
  -4.000   0.0382   0.01622   0.00866  -0.1276   0.9014   0.0877
  -3.750   0.0735   0.01550   0.00797  -0.1292   0.8991   0.1033
  -3.500   0.1095   0.01463   0.00731  -0.1311   0.8971   0.1461
  -3.250   0.1244   0.01413   0.00731  -0.1290   0.8896   0.2582
  -3.000   0.1555   0.01394   0.00728  -0.1297   0.8859   0.3337
  -2.750   0.1905   0.01385   0.00718  -0.1310   0.8833   0.3769
  -2.500   0.2265   0.01376   0.00707  -0.1325   0.8812   0.4090
  -2.250   0.2421   0.01397   0.00732  -0.1301   0.8734   0.4290
  -2.000   0.2733   0.01393   0.00724  -0.1307   0.8698   0.4540
  -1.750   0.3071   0.01379   0.00715  -0.1317   0.8672   0.4779
  -1.500   0.3310   0.01390   0.00727  -0.1308   0.8621   0.5014
  -1.250   0.3551   0.01391   0.00735  -0.1300   0.8566   0.5215
  -1.000   0.3865   0.01378   0.00725  -0.1306   0.8533   0.5421
  -0.750   0.4206   0.01363   0.00711  -0.1316   0.8507   0.5634
  -0.500   0.4381   0.01380   0.00735  -0.1297   0.8436   0.5816
  -0.250   0.4662   0.01369   0.00734  -0.1296   0.8393   0.6040
   0.000   0.4986   0.01349   0.00723  -0.1302   0.8362   0.6323
   0.250   0.5200   0.01352   0.00740  -0.1289   0.8304   0.6644
   0.500   0.5434   0.01343   0.00751  -0.1278   0.8250   0.7114
   0.750   0.5720   0.01309   0.00746  -0.1274   0.8216   0.7967
   1.000   0.6319   0.01266   0.00725  -0.1338   0.8199   1.0000
   1.250   0.6518   0.01299   0.00753  -0.1324   0.8128   1.0000
   1.500   0.6807   0.01307   0.00756  -0.1326   0.8080   1.0000
   1.750   0.7144   0.01306   0.00749  -0.1336   0.8046   1.0000
   2.000   0.7346   0.01334   0.00778  -0.1321   0.7971   1.0000
   2.250   0.7642   0.01337   0.00778  -0.1323   0.7919   1.0000
   2.500   0.7986   0.01329   0.00766  -0.1332   0.7878   1.0000
   2.750   0.8183   0.01345   0.00786  -0.1315   0.7784   1.0000
   3.000   0.8542   0.01319   0.00755  -0.1324   0.7724   1.0000
   3.250   0.8763   0.01319   0.00757  -0.1310   0.7616   1.0000
   3.500   0.9036   0.01300   0.00739  -0.1302   0.7508   1.0000
   3.750   0.9343   0.01271   0.00705  -0.1301   0.7399   1.0000
   4.000   0.9600   0.01258   0.00692  -0.1291   0.7282   1.0000
   4.250   0.9832   0.01255   0.00694  -0.1278   0.7164   1.0000
   4.500   1.0081   0.01248   0.00689  -0.1268   0.7040   1.0000
   4.750   1.0325   0.01239   0.00682  -0.1256   0.6901   1.0000
   5.000   1.0551   0.01232   0.00677  -0.1241   0.6737   1.0000
   5.250   1.0770   0.01229   0.00677  -0.1225   0.6550   1.0000
   5.500   1.0985   0.01228   0.00673  -0.1207   0.6325   1.0000
   5.750   1.1177   0.01236   0.00679  -0.1186   0.6052   1.0000
   6.000   1.1347   0.01254   0.00689  -0.1161   0.5684   1.0000
   6.250   1.1480   0.01292   0.00706  -0.1129   0.5157   1.0000
   6.500   1.1539   0.01366   0.00741  -0.1085   0.4451   1.0000
   6.750   1.1522   0.01477   0.00804  -0.1031   0.3648   1.0000
   7.000   1.1469   0.01602   0.00884  -0.0972   0.2925   1.0000
   7.250   1.1433   0.01736   0.00977  -0.0919   0.2281   1.0000
   7.500   1.1424   0.01875   0.01079  -0.0874   0.1767   1.0000
   7.750   1.1460   0.02002   0.01183  -0.0838   0.1413   1.0000
   8.000   1.1499   0.02136   0.01298  -0.0804   0.1193   1.0000
   8.250   1.1574   0.02255   0.01409  -0.0775   0.1035   1.0000
   8.500   1.1643   0.02384   0.01530  -0.0748   0.0920   1.0000
   8.750   1.1766   0.02484   0.01635  -0.0727   0.0837   1.0000
   9.000   1.1843   0.02623   0.01769  -0.0703   0.0770   1.0000
   9.250   1.1975   0.02724   0.01877  -0.0685   0.0716   1.0000
   9.500   1.2067   0.02873   0.02020  -0.0663   0.0668   1.0000
   9.750   1.2209   0.02987   0.02143  -0.0647   0.0631   1.0000
  10.000   1.2346   0.03098   0.02259  -0.0631   0.0592   1.0000
  10.250   1.2486   0.03250   0.02404  -0.0617   0.0555   1.0000
  10.500   1.2677   0.03386   0.02550  -0.0606   0.0531   1.0000
  10.750   1.2854   0.03509   0.02686  -0.0594   0.0509   1.0000
  11.000   1.3030   0.03640   0.02825  -0.0582   0.0486   1.0000
  11.250   1.3210   0.03778   0.02965  -0.0573   0.0466   1.0000
  11.500   1.3521   0.04018   0.03211  -0.0578   0.0441   1.0000
  11.750   1.3659   0.04172   0.03387  -0.0563   0.0431   1.0000
  12.000   1.3803   0.04355   0.03595  -0.0549   0.0420   1.0000
  12.250   1.3938   0.04562   0.03824  -0.0535   0.0411   1.0000
  12.500   1.4045   0.04792   0.04077  -0.0520   0.0402   1.0000
  12.750   1.4121   0.05018   0.04323  -0.0503   0.0394   1.0000
  13.000   1.4174   0.05237   0.04559  -0.0486   0.0386   1.0000
  13.250   1.4199   0.05475   0.04814  -0.0468   0.0379   1.0000
  13.500   1.4239   0.05713   0.05061  -0.0454   0.0370   1.0000
  13.750   1.4245   0.06085   0.05452  -0.0440   0.0364   1.0000
  14.000   1.4150   0.06534   0.05931  -0.0422   0.0361   1.0000
  14.250   1.3999   0.06993   0.06418  -0.0405   0.0359   1.0000
  14.500   1.3834   0.07426   0.06877  -0.0391   0.0359   1.0000
  14.750   1.3633   0.07911   0.07388  -0.0382   0.0359   1.0000
  15.000   1.3417   0.08419   0.07920  -0.0379   0.0359   1.0000
  15.250   1.3206   0.08927   0.08450  -0.0382   0.0359   1.0000
  15.500   1.2963   0.09510   0.09056  -0.0393   0.0359   1.0000
  15.750   1.2750   0.10071   0.09638  -0.0412   0.0361   1.0000
  16.000   1.2498   0.10745   0.10332  -0.0441   0.0362   1.0000
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