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-227 (fx83w227-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: FX 83-W-227 (fx83w227-il)
Reynolds number: 1,000,000
Max Cl/Cd: 73.5 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx83w227-il-1000000-n5.txt
Download as CSV file: xf-fx83w227-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -1.0270   0.06227   0.05800  -0.1094   0.9958   0.0334
 -19.500  -1.0267   0.05862   0.05428  -0.1120   0.9947   0.0340
 -19.250  -1.0244   0.05533   0.05093  -0.1143   0.9935   0.0348
 -19.000  -1.0204   0.05242   0.04795  -0.1162   0.9922   0.0354
 -18.750  -1.0158   0.04982   0.04529  -0.1176   0.9907   0.0363
 -18.500  -1.0088   0.04737   0.04278  -0.1190   0.9891   0.0368
 -18.250  -1.0018   0.04489   0.04023  -0.1207   0.9874   0.0373
 -18.000  -0.9936   0.04248   0.03778  -0.1224   0.9857   0.0381
 -17.750  -0.9833   0.04029   0.03554  -0.1241   0.9842   0.0386
 -17.500  -0.9700   0.03835   0.03356  -0.1258   0.9829   0.0394
 -17.250  -0.9549   0.03651   0.03167  -0.1276   0.9816   0.0402
 -17.000  -0.9486   0.03491   0.03002  -0.1273   0.9771   0.0410
 -16.750  -0.9348   0.03344   0.02850  -0.1281   0.9735   0.0417
 -16.250  -0.9093   0.03031   0.02530  -0.1297   0.9650   0.0432
 -16.000  -0.8922   0.02896   0.02391  -0.1309   0.9602   0.0439
 -15.750  -0.8693   0.02766   0.02257  -0.1330   0.9563   0.0452
 -15.500  -0.8480   0.02654   0.02141  -0.1344   0.9489   0.0462
 -15.250  -0.8181   0.02541   0.02022  -0.1375   0.9421   0.0472
 -15.000  -0.7877   0.02422   0.01900  -0.1409   0.9324   0.0486
 -14.750  -0.7477   0.02314   0.01787  -0.1459   0.9243   0.0504
 -14.500  -0.7085   0.02223   0.01688  -0.1504   0.9124   0.0515
 -14.250  -0.6719   0.02144   0.01599  -0.1542   0.8960   0.0527
 -13.750  -0.6291   0.01995   0.01427  -0.1560   0.8553   0.0552
 -13.500  -0.6154   0.01935   0.01357  -0.1550   0.8394   0.0561
 -13.250  -0.6018   0.01879   0.01294  -0.1539   0.8272   0.0571
 -13.000  -0.5884   0.01829   0.01235  -0.1526   0.8160   0.0582
 -12.750  -0.5748   0.01781   0.01180  -0.1513   0.8053   0.0588
 -12.500  -0.5634   0.01726   0.01120  -0.1496   0.7958   0.0603
 -12.250  -0.5509   0.01676   0.01066  -0.1481   0.7870   0.0617
 -12.000  -0.5379   0.01633   0.01017  -0.1464   0.7788   0.0628
 -11.750  -0.5238   0.01591   0.00971  -0.1449   0.7713   0.0642
 -11.500  -0.5099   0.01555   0.00929  -0.1433   0.7630   0.0652
 -11.250  -0.4963   0.01515   0.00885  -0.1416   0.7562   0.0668
 -11.000  -0.4829   0.01476   0.00844  -0.1398   0.7492   0.0684
 -10.500  -0.4544   0.01411   0.00771  -0.1362   0.7361   0.0718
 -10.250  -0.4391   0.01385   0.00740  -0.1345   0.7291   0.0730
  -9.750  -0.4110   0.01326   0.00677  -0.1305   0.7173   0.0770
  -9.500  -0.3958   0.01302   0.00649  -0.1286   0.7108   0.0791
  -9.250  -0.3810   0.01282   0.00625  -0.1266   0.7043   0.0813
  -9.000  -0.3660   0.01256   0.00599  -0.1246   0.6987   0.0840
  -8.750  -0.3509   0.01234   0.00575  -0.1226   0.6928   0.0866
  -8.500  -0.3357   0.01217   0.00554  -0.1204   0.6865   0.0889
  -8.250  -0.3198   0.01199   0.00534  -0.1184   0.6811   0.0914
  -8.000  -0.3052   0.01177   0.00513  -0.1162   0.6754   0.0954
  -7.750  -0.2903   0.01162   0.00495  -0.1139   0.6694   0.0986
  -7.500  -0.2750   0.01148   0.00478  -0.1117   0.6641   0.1015
  -7.250  -0.2602   0.01130   0.00461  -0.1093   0.6593   0.1053
  -7.000  -0.2458   0.01117   0.00446  -0.1068   0.6534   0.1090
  -6.750  -0.2326   0.01108   0.00434  -0.1040   0.6481   0.1127
  -6.500  -0.2200   0.01097   0.00424  -0.1011   0.6436   0.1172
  -6.250  -0.2052   0.01087   0.00414  -0.0986   0.6386   0.1217
  -6.000  -0.1885   0.01078   0.00403  -0.0965   0.6331   0.1259
  -5.750  -0.1731   0.01067   0.00392  -0.0941   0.6279   0.1320
  -5.250  -0.1361   0.01044   0.00371  -0.0906   0.6189   0.1435
  -5.000  -0.1181   0.01036   0.00362  -0.0887   0.6137   0.1495
  -4.750  -0.1012   0.01026   0.00352  -0.0866   0.6090   0.1568
  -4.500  -0.0816   0.01014   0.00343  -0.0850   0.6049   0.1650
  -4.250  -0.0634   0.01001   0.00333  -0.0832   0.6003   0.1746
  -4.000  -0.0454   0.00992   0.00325  -0.0813   0.5953   0.1838
  -3.750  -0.0291   0.00982   0.00316  -0.0790   0.5903   0.1959
  -3.500  -0.0104   0.00968   0.00307  -0.0773   0.5866   0.2094
  -3.250   0.0064   0.00954   0.00298  -0.0751   0.5822   0.2248
  -3.000   0.0210   0.00942   0.00289  -0.0725   0.5774   0.2390
  -2.750   0.0354   0.00932   0.00281  -0.0698   0.5728   0.2541
  -2.500   0.0527   0.00917   0.00273  -0.0677   0.5684   0.2735
  -2.250   0.0702   0.00903   0.00266  -0.0657   0.5642   0.2945
  -2.000   0.0867   0.00890   0.00260  -0.0635   0.5597   0.3172
  -1.750   0.1026   0.00882   0.00256  -0.0612   0.5546   0.3387
  -1.500   0.1216   0.00870   0.00252  -0.0595   0.5505   0.3636
  -1.000   0.1592   0.00853   0.00249  -0.0560   0.5411   0.4095
  -0.750   0.1765   0.00850   0.00249  -0.0540   0.5361   0.4316
  -0.500   0.1965   0.00842   0.00250  -0.0525   0.5318   0.4567
  -0.250   0.2168   0.00838   0.00251  -0.0511   0.5270   0.4798
   0.000   0.2359   0.00837   0.00255  -0.0494   0.5215   0.5013
   0.250   0.2544   0.00839   0.00260  -0.0477   0.5167   0.5210
   0.500   0.2758   0.00837   0.00264  -0.0465   0.5124   0.5389
   0.750   0.2959   0.00839   0.00269  -0.0450   0.5066   0.5557
   1.000   0.3153   0.00845   0.00276  -0.0434   0.5013   0.5701
   1.250   0.3353   0.00848   0.00283  -0.0420   0.4968   0.5884
   1.500   0.3565   0.00851   0.00290  -0.0408   0.4922   0.6039
   1.750   0.3763   0.00858   0.00298  -0.0393   0.4867   0.6161
   2.000   0.3947   0.00869   0.00309  -0.0376   0.4808   0.6265
   2.250   0.4171   0.00875   0.00317  -0.0366   0.4766   0.6369
   2.500   0.4379   0.00883   0.00326  -0.0354   0.4719   0.6461
   2.750   0.4571   0.00895   0.00338  -0.0339   0.4668   0.6546
   3.250   0.4980   0.00917   0.00361  -0.0314   0.4574   0.6691
   3.500   0.5185   0.00929   0.00373  -0.0301   0.4525   0.6772
   3.750   0.5366   0.00946   0.00389  -0.0285   0.4474   0.6838
   4.000   0.5561   0.00959   0.00403  -0.0271   0.4434   0.6912
   4.250   0.5774   0.00970   0.00417  -0.0261   0.4394   0.6989
   4.500   0.5968   0.00985   0.00432  -0.0247   0.4346   0.7068
   4.750   0.6134   0.01005   0.00453  -0.0228   0.4294   0.7156
   5.250   0.6528   0.01036   0.00488  -0.0203   0.4215   0.7309
   5.500   0.6721   0.01053   0.00507  -0.0190   0.4173   0.7388
   5.750   0.6888   0.01077   0.00531  -0.0173   0.4126   0.7460
   6.000   0.7061   0.01099   0.00555  -0.0156   0.4085   0.7540
   6.250   0.7261   0.01117   0.00576  -0.0145   0.4042   0.7623
   6.500   0.7438   0.01138   0.00601  -0.0130   0.4002   0.7713
   6.750   0.7602   0.01165   0.00629  -0.0114   0.3959   0.7807
   7.000   0.7759   0.01194   0.00660  -0.0096   0.3918   0.7903
   7.250   0.7946   0.01215   0.00686  -0.0083   0.3880   0.8019
   7.500   0.8116   0.01239   0.00715  -0.0068   0.3840   0.8148
   7.750   0.8277   0.01268   0.00749  -0.0052   0.3796   0.8300
   8.000   0.8419   0.01302   0.00790  -0.0033   0.3751   0.8507
   8.250   0.8683   0.01323   0.00827  -0.0038   0.3711   0.8866
   8.500   0.9336   0.01356   0.00872  -0.0127   0.3661   0.9211
   8.750   1.0018   0.01407   0.00925  -0.0224   0.3601   0.9392
   9.000   1.0576   0.01454   0.00974  -0.0293   0.3549   0.9562
   9.250   1.1010   0.01498   0.01019  -0.0336   0.3503   0.9746
   9.500   1.1287   0.01553   0.01073  -0.0348   0.3447   0.9867
  10.000   1.1784   0.01681   0.01200  -0.0359   0.3349   1.0000
  10.250   1.1909   0.01735   0.01254  -0.0341   0.3299   1.0000
  10.500   1.2007   0.01805   0.01323  -0.0320   0.3248   1.0000
  10.750   1.2140   0.01863   0.01382  -0.0304   0.3206   1.0000
  11.000   1.2273   0.01925   0.01445  -0.0289   0.3150   1.0000
  11.250   1.2340   0.02023   0.01539  -0.0267   0.3068   1.0000
  11.500   1.2466   0.02096   0.01612  -0.0253   0.3000   1.0000
  11.750   1.2509   0.02217   0.01727  -0.0231   0.2894   1.0000
  12.000   1.2610   0.02309   0.01819  -0.0215   0.2806   1.0000
  12.250   1.2701   0.02412   0.01920  -0.0200   0.2749   1.0000
  12.500   1.2810   0.02507   0.02017  -0.0187   0.2690   1.0000
  12.750   1.2914   0.02608   0.02118  -0.0174   0.2630   1.0000
  13.000   1.2980   0.02736   0.02245  -0.0158   0.2565   1.0000
  13.250   1.3079   0.02845   0.02354  -0.0146   0.2494   1.0000
  13.500   1.3152   0.02974   0.02483  -0.0133   0.2435   1.0000
  13.750   1.3212   0.03116   0.02624  -0.0119   0.2347   1.0000
  14.000   1.3265   0.03266   0.02774  -0.0105   0.2279   1.0000
  14.250   1.3317   0.03420   0.02926  -0.0092   0.2195   1.0000
  14.500   1.3354   0.03589   0.03095  -0.0079   0.2127   1.0000
  14.750   1.3377   0.03770   0.03274  -0.0066   0.2027   1.0000
  15.000   1.3365   0.03984   0.03486  -0.0052   0.1936   1.0000
  15.250   1.3353   0.04204   0.03704  -0.0039   0.1832   1.0000
  15.500   1.3374   0.04400   0.03899  -0.0028   0.1754   1.0000
  15.750   1.3293   0.04685   0.04180  -0.0013   0.1625   1.0000
  16.000   1.3255   0.04943   0.04435  -0.0002   0.1537   1.0000
  16.250   1.3223   0.05199   0.04689   0.0008   0.1433   1.0000
  16.500   1.3196   0.05458   0.04948   0.0017   0.1364   1.0000
  16.750   1.3140   0.05747   0.05235   0.0025   0.1278   1.0000
  17.000   1.3070   0.06055   0.05540   0.0033   0.1173   1.0000
  17.250   1.3014   0.06359   0.05844   0.0040   0.1094   1.0000
  17.500   1.2971   0.06652   0.06138   0.0044   0.1032   1.0000
  17.750   1.2897   0.06981   0.06465   0.0049   0.0948   1.0000
  18.000   1.2847   0.07295   0.06780   0.0052   0.0887   1.0000
  18.250   1.2810   0.07598   0.07083   0.0054   0.0834   1.0000
  18.500   1.2785   0.07895   0.07383   0.0055   0.0793   1.0000
  18.750   1.2743   0.08209   0.07698   0.0055   0.0750   1.0000
  19.000   1.2720   0.08509   0.08001   0.0054   0.0711   1.0000
  19.250   1.2699   0.08807   0.08302   0.0053   0.0683   1.0000
<< Back to FX 83-W-227 (fx83w227-il)

Polar data table (+)

Polar graphs


<< Back to FX 83-W-227 (fx83w227-il)