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

S8055 (12%) (s8055-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S8055 (12%) (s8055-il)
Reynolds number: 50,000
Max Cl/Cd: 32.73 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s8055-il-50000-n5.txt
Download as CSV file: xf-s8055-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8055 (12%)                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4366   0.10126   0.09407  -0.0417   1.0000   0.0456
 -10.250  -0.4378   0.09682   0.08970  -0.0436   1.0000   0.0453
 -10.000  -0.4411   0.09200   0.08495  -0.0459   1.0000   0.0449
  -9.750  -0.4475   0.08654   0.07956  -0.0489   1.0000   0.0445
  -9.500  -0.4567   0.08067   0.07376  -0.0526   1.0000   0.0439
  -9.250  -0.4732   0.07527   0.06841  -0.0557   1.0000   0.0433
  -9.000  -0.4951   0.07114   0.06431  -0.0565   1.0000   0.0426
  -8.750  -0.5224   0.06832   0.06153  -0.0541   1.0000   0.0422
  -8.500  -0.5475   0.06565   0.05883  -0.0510   1.0000   0.0418
  -8.250  -0.5700   0.06312   0.05622  -0.0474   1.0000   0.0413
  -8.000  -0.5882   0.06057   0.05354  -0.0438   1.0000   0.0414
  -7.750  -0.6022   0.05783   0.05060  -0.0404   1.0000   0.0412
  -7.500  -0.6114   0.05511   0.04765  -0.0373   1.0000   0.0414
  -7.250  -0.6165   0.05226   0.04452  -0.0344   1.0000   0.0415
  -7.000  -0.6177   0.04943   0.04136  -0.0317   1.0000   0.0417
  -6.750  -0.6151   0.04658   0.03815  -0.0292   1.0000   0.0420
  -6.500  -0.6088   0.04388   0.03505  -0.0269   1.0000   0.0424
  -6.250  -0.5992   0.04139   0.03217  -0.0248   1.0000   0.0430
  -6.000  -0.5866   0.03906   0.02942  -0.0229   1.0000   0.0438
  -5.750  -0.5676   0.03679   0.02663  -0.0217   0.9987   0.0458
  -5.500  -0.5400   0.03490   0.02455  -0.0225   0.9945   0.0489
  -5.250  -0.5119   0.03333   0.02274  -0.0230   0.9902   0.0529
  -5.000  -0.4816   0.03172   0.02080  -0.0233   0.9862   0.0571
  -4.750  -0.4530   0.03049   0.01954  -0.0239   0.9820   0.0646
  -4.500  -0.4251   0.02929   0.01827  -0.0242   0.9773   0.0737
  -4.250  -0.3950   0.02820   0.01712  -0.0248   0.9730   0.0898
  -4.000  -0.3683   0.02708   0.01607  -0.0251   0.9681   0.1154
  -3.750  -0.3414   0.02579   0.01511  -0.0257   0.9630   0.1710
  -3.500  -0.3146   0.02443   0.01446  -0.0266   0.9584   0.2902
  -3.250  -0.2976   0.02334   0.01419  -0.0251   0.9522   0.4400
  -3.000  -0.2774   0.02287   0.01459  -0.0223   0.9468   0.6159
  -2.750  -0.2530   0.02315   0.01504  -0.0198   0.9416   0.7386
  -2.500  -0.2287   0.02349   0.01528  -0.0177   0.9353   0.8090
  -2.250  -0.1895   0.02394   0.01552  -0.0184   0.9309   0.8652
  -2.000  -0.1310   0.02446   0.01571  -0.0230   0.9287   0.9080
  -1.750  -0.0668   0.02483   0.01574  -0.0296   0.9257   0.9380
  -1.500   0.0013   0.02504   0.01563  -0.0375   0.9228   0.9606
  -1.250   0.0661   0.02510   0.01542  -0.0452   0.9193   0.9800
  -1.000   0.1310   0.02508   0.01518  -0.0531   0.9161   0.9965
  -0.750   0.1622   0.02511   0.01508  -0.0548   0.9081   1.0000
  -0.500   0.1922   0.02517   0.01501  -0.0561   0.9001   1.0000
  -0.250   0.2110   0.02527   0.01503  -0.0553   0.8898   1.0000
   0.000   0.2465   0.02533   0.01498  -0.0573   0.8829   1.0000
   0.250   0.2606   0.02547   0.01507  -0.0555   0.8711   1.0000
   0.500   0.2815   0.02559   0.01513  -0.0547   0.8609   1.0000
   0.750   0.3124   0.02563   0.01511  -0.0555   0.8523   1.0000
   1.000   0.3272   0.02578   0.01522  -0.0535   0.8399   1.0000
   1.250   0.3469   0.02589   0.01530  -0.0523   0.8286   1.0000
   1.500   0.3807   0.02583   0.01522  -0.0532   0.8200   1.0000
   1.750   0.3953   0.02596   0.01534  -0.0510   0.8066   1.0000
   2.000   0.4130   0.02606   0.01542  -0.0491   0.7936   1.0000
   2.250   0.4343   0.02608   0.01544  -0.0478   0.7809   1.0000
   2.500   0.4604   0.02598   0.01535  -0.0470   0.7689   1.0000
   2.750   0.4891   0.02577   0.01516  -0.0465   0.7572   1.0000
   3.000   0.5086   0.02571   0.01511  -0.0446   0.7424   1.0000
   3.250   0.5295   0.02560   0.01502  -0.0429   0.7274   1.0000
   3.500   0.5517   0.02542   0.01489  -0.0412   0.7121   1.0000
   3.750   0.5751   0.02518   0.01470  -0.0397   0.6964   1.0000
   4.000   0.5957   0.02501   0.01457  -0.0378   0.6788   1.0000
   4.250   0.6165   0.02486   0.01447  -0.0360   0.6600   1.0000
   4.500   0.6407   0.02459   0.01427  -0.0345   0.6407   1.0000
   4.750   0.6686   0.02420   0.01390  -0.0333   0.6207   1.0000
   5.000   0.6902   0.02411   0.01384  -0.0316   0.5964   1.0000
   5.250   0.7167   0.02389   0.01363  -0.0303   0.5712   1.0000
   5.500   0.7415   0.02381   0.01351  -0.0290   0.5432   1.0000
   5.750   0.7638   0.02393   0.01356  -0.0274   0.5129   1.0000
   6.000   0.7849   0.02417   0.01372  -0.0258   0.4813   1.0000
   6.250   0.8042   0.02457   0.01400  -0.0240   0.4500   1.0000
   6.500   0.8219   0.02511   0.01442  -0.0222   0.4194   1.0000
   6.750   0.8385   0.02575   0.01495  -0.0204   0.3903   1.0000
   7.000   0.8548   0.02648   0.01560  -0.0186   0.3636   1.0000
   7.250   0.8711   0.02727   0.01627  -0.0170   0.3397   1.0000
   7.500   0.8870   0.02812   0.01707  -0.0154   0.3170   1.0000
   7.750   0.9031   0.02900   0.01787  -0.0138   0.2968   1.0000
   8.000   0.9195   0.02992   0.01875  -0.0124   0.2781   1.0000
   8.250   0.9357   0.03087   0.01971  -0.0110   0.2606   1.0000
   8.500   0.9527   0.03186   0.02071  -0.0098   0.2447   1.0000
   8.750   0.9687   0.03287   0.02176  -0.0084   0.2297   1.0000
   9.000   0.9851   0.03392   0.02283  -0.0072   0.2161   1.0000
   9.250   1.0010   0.03500   0.02391  -0.0059   0.2035   1.0000
   9.500   1.0151   0.03614   0.02513  -0.0044   0.1912   1.0000
   9.750   1.0293   0.03739   0.02654  -0.0031   0.1797   1.0000
  10.000   1.0425   0.03868   0.02791  -0.0017   0.1692   1.0000
  10.250   1.0573   0.03994   0.02912  -0.0005   0.1599   1.0000
  10.500   1.0677   0.04146   0.03088   0.0010   0.1507   1.0000
  10.750   1.0803   0.04295   0.03245   0.0023   0.1429   1.0000
  11.000   1.0911   0.04458   0.03424   0.0036   0.1356   1.0000
  11.250   1.1021   0.04629   0.03608   0.0048   0.1292   1.0000
  11.500   1.1084   0.04823   0.03825   0.0062   0.1231   1.0000
  11.750   1.1228   0.04979   0.03976   0.0071   0.1181   1.0000
  12.000   1.1221   0.05250   0.04288   0.0086   0.1137   1.0000
  12.250   1.1241   0.05484   0.04544   0.0099   0.1095   1.0000
  12.500   1.1364   0.05644   0.04699   0.0106   0.1054   1.0000
  12.750   1.1264   0.05992   0.05083   0.0118   0.1027   1.0000
  13.000   1.1149   0.06376   0.05502   0.0125   0.1005   1.0000
  13.250   1.1022   0.06790   0.05944   0.0128   0.0986   1.0000
  13.500   1.0884   0.07233   0.06408   0.0125   0.0969   1.0000
  13.750   1.0740   0.07705   0.06899   0.0116   0.0954   1.0000
  14.000   1.0901   0.07836   0.07023   0.0122   0.0924   1.0000
  14.250   1.0571   0.08577   0.07790   0.0096   0.0922   1.0000
  14.500   1.0166   0.09536   0.08770   0.0048   0.0923   1.0000
<< Back to S8055 (12%) (s8055-il)

Polar data table (+)

Polar graphs


<< Back to S8055 (12%) (s8055-il)