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FX 83-W-227 (fx83w227-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 83-W-227 (fx83w227-il)
Reynolds number: 100,000
Max Cl/Cd: 8.94 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx83w227-il-100000.txt
Download as CSV file: xf-fx83w227-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 83-W-227                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.5791   0.09732   0.09216  -0.0737   0.9896   0.1365
 -12.750  -0.6472   0.08306   0.07773  -0.0811   0.9846   0.1351
 -12.500  -0.7197   0.07250   0.06687  -0.0851   0.9774   0.1335
 -12.250  -0.7720   0.06602   0.06003  -0.0860   0.9698   0.1331
 -12.000  -0.8119   0.06247   0.05620  -0.0828   0.9594   0.1333
 -11.750  -0.8451   0.06012   0.05357  -0.0778   0.9497   0.1336
 -11.500  -0.8654   0.05754   0.05063  -0.0743   0.9421   0.1346
 -11.250  -0.8895   0.05573   0.04851  -0.0685   0.9318   0.1355
 -11.000  -0.8848   0.05298   0.04540  -0.0675   0.9261   0.1373
 -10.750  -0.8792   0.05178   0.04423  -0.0650   0.9175   0.1392
 -10.500  -0.8529   0.05056   0.04298  -0.0660   0.9123   0.1424
 -10.250  -0.8432   0.04926   0.04150  -0.0643   0.9062   0.1452
 -10.000  -0.8453   0.04804   0.04002  -0.0606   0.8976   0.1475
  -9.750  -0.8319   0.04639   0.03788  -0.0595   0.8927   0.1506
  -9.500  -0.8274   0.04537   0.03694  -0.0565   0.8846   0.1529
  -9.250  -0.8029   0.04450   0.03608  -0.0567   0.8791   0.1568
  -9.000  -0.7723   0.04331   0.03469  -0.0579   0.8752   0.1620
  -8.750  -0.7815   0.04292   0.03408  -0.0523   0.8657   0.1642
  -8.500  -0.7547   0.04173   0.03287  -0.0528   0.8607   0.1688
  -8.250  -0.7182   0.04087   0.03200  -0.0548   0.8573   0.1754
  -8.000  -0.7245   0.04070   0.03168  -0.0496   0.8483   0.1787
  -7.750  -0.7011   0.03980   0.03071  -0.0494   0.8427   0.1843
  -7.500  -0.6627   0.03899   0.02995  -0.0515   0.8392   0.1925
  -7.250  -0.6661   0.03899   0.02977  -0.0468   0.8311   0.1971
  -7.000  -0.6442   0.03835   0.02925  -0.0463   0.8249   0.2040
  -6.750  -0.6118   0.03769   0.02846  -0.0473   0.8209   0.2147
  -6.500  -0.5677   0.03676   0.02769  -0.0503   0.8185   0.2275
  -6.250  -0.5925   0.03731   0.02819  -0.0422   0.8071   0.2303
  -6.000  -0.5600   0.03660   0.02758  -0.0431   0.8028   0.2435
  -5.750  -0.5205   0.03580   0.02686  -0.0452   0.8000   0.2609
  -5.500  -0.5422   0.03644   0.02747  -0.0377   0.7893   0.2661
  -5.250  -0.5172   0.03594   0.02708  -0.0374   0.7845   0.2841
  -5.000  -0.4818   0.03519   0.02647  -0.0386   0.7815   0.3099
  -4.750  -0.4976   0.03572   0.02710  -0.0322   0.7714   0.3203
  -4.500  -0.4797   0.03537   0.02691  -0.0307   0.7661   0.3482
  -4.250  -0.4496   0.03468   0.02650  -0.0307   0.7628   0.3890
  -4.000  -0.4610   0.03517   0.02717  -0.0249   0.7535   0.4116
  -3.750  -0.4482   0.03505   0.02730  -0.0224   0.7476   0.4530
  -3.500  -0.4206   0.03481   0.02729  -0.0216   0.7441   0.5044
  -3.250  -0.4239   0.03551   0.02813  -0.0169   0.7360   0.5338
  -3.000  -0.4136   0.03593   0.02865  -0.0139   0.7291   0.5670
  -2.750  -0.3821   0.03601   0.02877  -0.0135   0.7253   0.6040
  -2.500  -0.3416   0.03607   0.02884  -0.0142   0.7230   0.6364
  -2.250  -0.3723   0.03756   0.03041  -0.0064   0.7108   0.6481
  -2.000  -0.3398   0.03774   0.03057  -0.0060   0.7067   0.6739
  -1.750  -0.2992   0.03773   0.03052  -0.0068   0.7043   0.6989
  -1.500  -0.3275   0.03932   0.03218   0.0005   0.6925   0.7101
  -1.250  -0.2979   0.03954   0.03238   0.0011   0.6884   0.7304
  -1.000  -0.2570   0.03949   0.03230   0.0004   0.6858   0.7508
  -0.750  -0.2853   0.04091   0.03374   0.0075   0.6742   0.7651
  -0.500  -0.2583   0.04115   0.03395   0.0084   0.6700   0.7834
  -0.250  -0.2188   0.04116   0.03394   0.0078   0.6673   0.8016
   0.000  -0.2375   0.04270   0.03555   0.0132   0.6569   0.8151
   0.250  -0.2101   0.04298   0.03582   0.0138   0.6518   0.8335
   0.500  -0.1659   0.04301   0.03581   0.0124   0.6490   0.8522
   0.750  -0.1111   0.04299   0.03572   0.0095   0.6471   0.8693
   1.000  -0.1455   0.04543   0.03824   0.0155   0.6341   0.8853
   1.250  -0.0739   0.04596   0.03871   0.0089   0.6310   0.8959
   1.500  -0.0059   0.04593   0.03857   0.0033   0.6290   0.9063
   1.750  -0.0143   0.04914   0.04185   0.0041   0.6165   0.9174
   2.000   0.0499   0.04954   0.04216  -0.0019   0.6131   0.9245
   2.250   0.1294   0.04947   0.04199  -0.0099   0.6110   0.9289
   2.500   0.1907   0.04892   0.04135  -0.0145   0.6096   0.9380
   2.750   0.1791   0.05315   0.04566  -0.0148   0.5951   0.9464
   3.000   0.2380   0.05278   0.04522  -0.0195   0.5929   0.9548
   3.250   0.3114   0.05204   0.04441  -0.0263   0.5915   0.9594
   3.500   0.2909   0.05649   0.04893  -0.0256   0.5770   0.9709
   3.750   0.3517   0.05617   0.04856  -0.0311   0.5748   0.9774
   4.000   0.4158   0.05540   0.04775  -0.0366   0.5732   0.9833
   4.250   0.4847   0.05419   0.04648  -0.0426   0.5722   0.9887
   4.500   0.4624   0.05978   0.05217  -0.0432   0.5566   0.9991
   4.750   0.4543   0.06084   0.05320  -0.0401   0.5515   1.0000
   5.000   0.3809   0.06417   0.05653  -0.0309   0.5409   1.0000
   5.250   0.3860   0.06314   0.05542  -0.0272   0.5380   1.0000
   5.500   0.3313   0.06590   0.05812  -0.0195   0.5295   1.0000
   5.750   0.3201   0.06764   0.05980  -0.0164   0.5239   1.0000
   6.000   0.3416   0.06777   0.05985  -0.0154   0.5206   1.0000
   6.250   0.3781   0.06707   0.05907  -0.0154   0.5184   1.0000
   6.500   0.3238   0.07248   0.06449  -0.0108   0.5077   1.0000
   6.750   0.3382   0.07354   0.06551  -0.0100   0.5038   1.0000
   7.000   0.3704   0.07343   0.06535  -0.0099   0.5011   1.0000
   7.250   0.4144   0.07253   0.06439  -0.0103   0.4993   1.0000
   7.500   0.3425   0.07973   0.07164  -0.0061   0.4883   1.0000
   7.750   0.3636   0.08057   0.07246  -0.0057   0.4848   1.0000
   8.000   0.4035   0.08007   0.07191  -0.0060   0.4822   1.0000
   8.250   0.3606   0.08555   0.07743  -0.0035   0.4747   1.0000
   8.500   0.3152   0.09740   0.08943  -0.0053   0.5165   1.0000
   8.750   0.3052   0.10015   0.09219  -0.0042   0.5159   1.0000
   9.000   0.2844   0.10180   0.09386  -0.0021   0.5080   1.0000
   9.250   0.3089   0.10320   0.09525  -0.0023   0.5026   1.0000
   9.500   0.3625   0.10527   0.09729  -0.0041   0.4988   1.0000
   9.750   0.3150   0.10750   0.09956  -0.0013   0.4931   1.0000
  10.000   0.3291   0.10901   0.10107  -0.0011   0.4864   1.0000
  10.250   0.3708   0.11067   0.10272  -0.0021   0.4823   1.0000
  10.500   0.3777   0.11366   0.10572  -0.0021   0.4802   1.0000
  10.750   0.3572   0.11478   0.10686  -0.0004   0.4691   1.0000
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