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S7055 (10.5%) Flat-Bottomed (s7055-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S7055 (10.5%) Flat-Bottomed (s7055-il)
Reynolds number: 200,000
Max Cl/Cd: 77.28 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s7055-il-200000.txt
Download as CSV file: xf-s7055-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S7055 (10.5%) Flat-Bottomed                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3283   0.08876   0.08552  -0.0408   1.0000   0.0421
  -8.250  -0.3295   0.08663   0.08346  -0.0399   1.0000   0.0440
  -8.000  -0.3426   0.08497   0.08189  -0.0378   1.0000   0.0440
  -7.750  -0.3689   0.08458   0.08162  -0.0329   1.0000   0.0439
  -7.500  -0.3818   0.08289   0.08000  -0.0321   0.9980   0.0452
  -7.250  -0.3607   0.07607   0.07315  -0.0460   0.9878   0.0489
  -7.000  -0.3333   0.06733   0.06404  -0.0659   0.9757   0.0508
  -6.750  -0.3187   0.05976   0.05650  -0.0699   0.9716   0.0524
  -6.500  -0.2958   0.05673   0.05347  -0.0717   0.9666   0.0540
  -6.250  -0.2707   0.05287   0.04951  -0.0756   0.9606   0.0568
  -6.000  -0.2382   0.04900   0.04476  -0.0829   0.9528   0.0640
  -5.750  -0.2211   0.04213   0.03805  -0.0851   0.9470   0.0665
  -5.500  -0.1906   0.03914   0.03498  -0.0876   0.9431   0.0697
  -5.250  -0.1748   0.03149   0.02634  -0.0868   0.9330   0.0535
  -5.000  -0.1467   0.02656   0.02082  -0.0870   0.9282   0.0444
  -4.750  -0.1271   0.02297   0.01649  -0.0850   0.9191   0.0420
  -4.500  -0.0966   0.02106   0.01425  -0.0852   0.9142   0.0434
  -4.250  -0.0728   0.02001   0.01299  -0.0842   0.9056   0.0468
  -4.000  -0.0426   0.01923   0.01187  -0.0839   0.9000   0.0508
  -3.750  -0.0199   0.01737   0.00994  -0.0828   0.8914   0.0554
  -3.500   0.0084   0.01678   0.00921  -0.0824   0.8855   0.0631
  -3.250   0.0312   0.01582   0.00825  -0.0813   0.8766   0.0706
  -3.000   0.0582   0.01520   0.00753  -0.0807   0.8708   0.0795
  -2.750   0.0813   0.01471   0.00707  -0.0797   0.8615   0.0888
  -2.500   0.1068   0.01407   0.00643  -0.0788   0.8554   0.0988
  -2.250   0.1299   0.01360   0.00599  -0.0777   0.8461   0.1142
  -2.000   0.1532   0.01286   0.00552  -0.0767   0.8389   0.1718
  -1.750   0.1681   0.01145   0.00534  -0.0746   0.8303   0.4845
  -1.500   0.1825   0.01049   0.00538  -0.0710   0.8223   0.7623
  -1.250   0.2672   0.01018   0.00521  -0.0810   0.8180   0.9673
  -1.000   0.3415   0.01001   0.00478  -0.0903   0.8132   1.0000
  -0.750   0.3627   0.01002   0.00467  -0.0890   0.8026   1.0000
  -0.500   0.3849   0.01002   0.00455  -0.0878   0.7933   1.0000
  -0.250   0.4081   0.01000   0.00439  -0.0867   0.7849   1.0000
   0.000   0.4304   0.01004   0.00433  -0.0856   0.7744   1.0000
   0.250   0.4537   0.01006   0.00425  -0.0846   0.7651   1.0000
   0.500   0.4778   0.01007   0.00413  -0.0837   0.7564   1.0000
   0.750   0.5010   0.01012   0.00412  -0.0827   0.7458   1.0000
   1.000   0.5249   0.01017   0.00408  -0.0818   0.7360   1.0000
   1.250   0.5496   0.01021   0.00400  -0.0809   0.7270   1.0000
   1.500   0.5733   0.01028   0.00402  -0.0800   0.7158   1.0000
   1.750   0.5973   0.01036   0.00405  -0.0792   0.7050   1.0000
   2.000   0.6217   0.01044   0.00405  -0.0784   0.6946   1.0000
   2.250   0.6467   0.01052   0.00404  -0.0776   0.6846   1.0000
   2.500   0.6705   0.01062   0.00411  -0.0768   0.6727   1.0000
   2.750   0.6946   0.01074   0.00420  -0.0759   0.6612   1.0000
   3.000   0.7190   0.01086   0.00428  -0.0752   0.6499   1.0000
   3.250   0.7435   0.01099   0.00435  -0.0744   0.6387   1.0000
   3.500   0.7682   0.01112   0.00443  -0.0737   0.6273   1.0000
   3.750   0.7922   0.01126   0.00455  -0.0728   0.6145   1.0000
   4.000   0.8161   0.01141   0.00469  -0.0720   0.6015   1.0000
   4.250   0.8401   0.01157   0.00484  -0.0712   0.5885   1.0000
   4.500   0.8640   0.01175   0.00501  -0.0704   0.5755   1.0000
   4.750   0.8880   0.01193   0.00519  -0.0696   0.5624   1.0000
   5.000   0.9118   0.01213   0.00537  -0.0688   0.5489   1.0000
   5.250   0.9354   0.01234   0.00557  -0.0680   0.5350   1.0000
   5.500   0.9588   0.01256   0.00581  -0.0671   0.5206   1.0000
   5.750   0.9818   0.01279   0.00604  -0.0662   0.5057   1.0000
   6.000   1.0047   0.01303   0.00629  -0.0653   0.4905   1.0000
   6.250   1.0273   0.01330   0.00655  -0.0643   0.4749   1.0000
   6.500   1.0494   0.01358   0.00684  -0.0633   0.4588   1.0000
   6.750   1.0712   0.01390   0.00714  -0.0623   0.4425   1.0000
   7.000   1.0923   0.01421   0.00748  -0.0611   0.4245   1.0000
   7.250   1.1129   0.01454   0.00784  -0.0599   0.4061   1.0000
   7.500   1.1329   0.01492   0.00822  -0.0586   0.3876   1.0000
   7.750   1.1522   0.01533   0.00865  -0.0572   0.3684   1.0000
   8.000   1.1706   0.01576   0.00909  -0.0557   0.3476   1.0000
   8.250   1.1875   0.01625   0.00956  -0.0540   0.3261   1.0000
   8.500   1.2035   0.01678   0.01007  -0.0521   0.3028   1.0000
   8.750   1.2183   0.01736   0.01064  -0.0502   0.2794   1.0000
   9.000   1.2312   0.01803   0.01126  -0.0480   0.2563   1.0000
   9.250   1.2428   0.01875   0.01197  -0.0457   0.2321   1.0000
   9.500   1.2512   0.01954   0.01270  -0.0429   0.2063   1.0000
   9.750   1.2560   0.02046   0.01352  -0.0396   0.1797   1.0000
  10.000   1.2591   0.02158   0.01450  -0.0364   0.1511   1.0000
  10.250   1.2620   0.02283   0.01561  -0.0335   0.1243   1.0000
  10.500   1.2646   0.02423   0.01690  -0.0308   0.1005   1.0000
  10.750   1.2652   0.02586   0.01843  -0.0281   0.0795   1.0000
  11.000   1.2615   0.02792   0.02035  -0.0253   0.0599   1.0000
  11.250   1.2549   0.03036   0.02273  -0.0226   0.0424   1.0000
  11.500   1.2484   0.03294   0.02530  -0.0202   0.0328   1.0000
  11.750   1.2390   0.03592   0.02833  -0.0181   0.0276   1.0000
  12.000   1.2385   0.03828   0.03082  -0.0167   0.0244   1.0000
  12.250   1.2351   0.04099   0.03361  -0.0156   0.0225   1.0000
  12.500   1.2275   0.04425   0.03694  -0.0144   0.0214   1.0000
  12.750   1.2222   0.04744   0.04023  -0.0134   0.0202   1.0000
  13.000   1.2235   0.05003   0.04295  -0.0126   0.0195   1.0000
  13.250   1.2248   0.05270   0.04575  -0.0119   0.0187   1.0000
  13.500   1.2269   0.05535   0.04852  -0.0113   0.0180   1.0000
  13.750   1.2300   0.05798   0.05127  -0.0107   0.0176   1.0000
  14.000   1.2322   0.06078   0.05418  -0.0102   0.0170   1.0000
  14.250   1.2349   0.06364   0.05716  -0.0098   0.0165   1.0000
  14.500   1.2375   0.06661   0.06027  -0.0095   0.0163   1.0000
  14.750   1.2384   0.06988   0.06369  -0.0093   0.0160   1.0000
  15.000   1.2379   0.07345   0.06744  -0.0095   0.0159   1.0000
  15.250   1.2351   0.07738   0.07152  -0.0098   0.0154   1.0000
  15.500   1.2292   0.08193   0.07627  -0.0105   0.0152   1.0000
  15.750   1.2204   0.08696   0.08151  -0.0118   0.0151   1.0000
  16.000   1.2053   0.09319   0.08797  -0.0138   0.0149   1.0000
  16.250   1.1914   0.09927   0.09427  -0.0163   0.0148   1.0000
  16.500   1.1846   0.10420   0.09938  -0.0187   0.0150   1.0000
  16.750   1.1632   0.11216   0.10757  -0.0227   0.0148   1.0000
  17.000   1.1557   0.11767   0.11324  -0.0259   0.0150   1.0000
  17.250   1.1381   0.12548   0.12124  -0.0305   0.0149   1.0000
  17.500   1.1269   0.13239   0.12833  -0.0350   0.0151   1.0000
  17.750   1.1095   0.14095   0.13705  -0.0404   0.0151   1.0000
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