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USA-35B AIRFOIL (usa35b-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: USA-35B AIRFOIL (usa35b-il)
Reynolds number: 200,000
Max Cl/Cd: 76.76 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa35b-il-200000.txt
Download as CSV file: xf-usa35b-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA-35B AIRFOIL                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3212   0.08954   0.08599  -0.0362   1.0000   0.0669
  -9.500  -0.3347   0.08762   0.08416  -0.0349   1.0000   0.0683
  -9.250  -0.3622   0.08669   0.08334  -0.0315   1.0000   0.0690
  -9.000  -0.3990   0.08479   0.08155  -0.0329   0.9993   0.0701
  -8.750  -0.3767   0.07574   0.07242  -0.0472   0.9927   0.0715
  -8.500  -0.3529   0.07358   0.07028  -0.0462   0.9890   0.0726
  -8.250  -0.3245   0.07063   0.06731  -0.0492   0.9848   0.0746
  -8.000  -0.2905   0.05931   0.05548  -0.0722   0.9730   0.0826
  -7.750  -0.2598   0.05604   0.05232  -0.0740   0.9703   0.0837
  -7.500  -0.2326   0.05357   0.04987  -0.0757   0.9633   0.0853
  -7.250  -0.1914   0.04770   0.04325  -0.0872   0.9568   0.0954
  -7.000  -0.1639   0.04395   0.03968  -0.0888   0.9506   0.0969
  -6.750  -0.1320   0.04167   0.03743  -0.0909   0.9443   0.0993
  -6.500  -0.0990   0.03825   0.03353  -0.0951   0.9360   0.1108
  -6.250  -0.0703   0.03590   0.03125  -0.0961   0.9274   0.1132
  -6.000  -0.0399   0.02532   0.01909  -0.0975   0.9172   0.0684
  -5.750  -0.0092   0.02270   0.01609  -0.0980   0.9086   0.0659
  -5.500   0.0175   0.02101   0.01409  -0.0974   0.8958   0.0656
  -5.250   0.0452   0.01978   0.01264  -0.0970   0.8833   0.0665
  -5.000   0.0730   0.01858   0.01118  -0.0964   0.8708   0.0668
  -4.750   0.1005   0.01755   0.00993  -0.0956   0.8574   0.0673
  -4.500   0.1271   0.01673   0.00894  -0.0949   0.8420   0.0682
  -4.250   0.1539   0.01606   0.00812  -0.0941   0.8266   0.0695
  -4.000   0.1806   0.01540   0.00734  -0.0934   0.8113   0.0713
  -3.750   0.2070   0.01477   0.00673  -0.0929   0.7965   0.0748
  -3.500   0.2339   0.01438   0.00628  -0.0924   0.7823   0.0788
  -3.250   0.2608   0.01393   0.00574  -0.0918   0.7684   0.0829
  -3.000   0.2873   0.01346   0.00527  -0.0912   0.7545   0.0902
  -2.750   0.3139   0.01303   0.00483  -0.0907   0.7406   0.1046
  -2.500   0.3404   0.01244   0.00446  -0.0904   0.7273   0.1540
  -2.250   0.3655   0.01161   0.00433  -0.0902   0.7162   0.3448
  -2.000   0.3848   0.01057   0.00439  -0.0883   0.7067   0.6733
  -1.750   0.4305   0.00999   0.00434  -0.0906   0.6955   1.0000
  -1.500   0.4572   0.01014   0.00428  -0.0902   0.6862   1.0000
  -1.250   0.4839   0.01027   0.00426  -0.0898   0.6766   1.0000
  -1.000   0.5108   0.01043   0.00428  -0.0895   0.6677   1.0000
  -0.750   0.5378   0.01059   0.00430  -0.0891   0.6589   1.0000
  -0.500   0.5648   0.01076   0.00436  -0.0888   0.6502   1.0000
  -0.250   0.5920   0.01094   0.00442  -0.0885   0.6420   1.0000
   0.000   0.6190   0.01113   0.00453  -0.0882   0.6335   1.0000
   0.250   0.6461   0.01131   0.00460  -0.0879   0.6251   1.0000
   0.500   0.6731   0.01150   0.00474  -0.0877   0.6168   1.0000
   0.750   0.7003   0.01169   0.00485  -0.0874   0.6086   1.0000
   1.000   0.7273   0.01190   0.00500  -0.0871   0.6002   1.0000
   1.250   0.7543   0.01208   0.00512  -0.0868   0.5915   1.0000
   1.500   0.7811   0.01229   0.00530  -0.0865   0.5829   1.0000
   1.750   0.8080   0.01247   0.00541  -0.0861   0.5737   1.0000
   2.000   0.8340   0.01262   0.00555  -0.0856   0.5622   1.0000
   2.250   0.8600   0.01275   0.00561  -0.0851   0.5500   1.0000
   2.500   0.8861   0.01288   0.00565  -0.0845   0.5379   1.0000
   2.750   0.9118   0.01301   0.00582  -0.0840   0.5259   1.0000
   3.000   0.9379   0.01319   0.00597  -0.0836   0.5152   1.0000
   3.250   0.9640   0.01337   0.00609  -0.0831   0.5049   1.0000
   3.500   0.9895   0.01353   0.00631  -0.0826   0.4928   1.0000
   3.750   1.0151   0.01372   0.00649  -0.0820   0.4810   1.0000
   4.000   1.0404   0.01392   0.00664  -0.0815   0.4692   1.0000
   4.250   1.0654   0.01412   0.00684  -0.0809   0.4562   1.0000
   4.500   1.0902   0.01433   0.00707  -0.0802   0.4428   1.0000
   4.750   1.1148   0.01458   0.00732  -0.0796   0.4296   1.0000
   5.000   1.1391   0.01485   0.00758  -0.0789   0.4166   1.0000
   5.250   1.1629   0.01515   0.00786  -0.0781   0.4029   1.0000
   5.500   1.1858   0.01546   0.00814  -0.0773   0.3873   1.0000
   5.750   1.2080   0.01582   0.00846  -0.0763   0.3704   1.0000
   6.000   1.2297   0.01622   0.00884  -0.0752   0.3536   1.0000
   6.250   1.2510   0.01667   0.00925  -0.0742   0.3376   1.0000
   6.500   1.2717   0.01716   0.00971  -0.0731   0.3215   1.0000
   6.750   1.2919   0.01768   0.01021  -0.0719   0.3056   1.0000
   7.000   1.3114   0.01822   0.01073  -0.0706   0.2898   1.0000
   7.250   1.3302   0.01878   0.01128  -0.0693   0.2742   1.0000
   7.500   1.3483   0.01936   0.01185  -0.0678   0.2587   1.0000
   7.750   1.3656   0.01996   0.01246  -0.0663   0.2440   1.0000
   8.000   1.3819   0.02062   0.01310  -0.0647   0.2310   1.0000
   8.250   1.3970   0.02132   0.01378  -0.0629   0.2188   1.0000
   8.500   1.4112   0.02198   0.01447  -0.0609   0.2064   1.0000
   8.750   1.4232   0.02271   0.01523  -0.0587   0.1945   1.0000
   9.000   1.4342   0.02355   0.01609  -0.0565   0.1832   1.0000
   9.250   1.4434   0.02452   0.01706  -0.0543   0.1715   1.0000
   9.500   1.4511   0.02564   0.01818  -0.0520   0.1583   1.0000
   9.750   1.4576   0.02692   0.01947  -0.0498   0.1418   1.0000
  10.000   1.4596   0.02860   0.02110  -0.0475   0.1216   1.0000
  10.250   1.4594   0.03060   0.02302  -0.0453   0.0998   1.0000
  10.500   1.4572   0.03291   0.02524  -0.0433   0.0846   1.0000
  10.750   1.4559   0.03528   0.02758  -0.0417   0.0760   1.0000
  11.000   1.4540   0.03783   0.03016  -0.0403   0.0710   1.0000
  11.250   1.4509   0.04062   0.03299  -0.0392   0.0674   1.0000
  11.500   1.4444   0.04388   0.03626  -0.0382   0.0647   1.0000
  11.750   1.4435   0.04669   0.03920  -0.0376   0.0623   1.0000
  12.000   1.4405   0.04978   0.04238  -0.0371   0.0602   1.0000
  12.250   1.4352   0.05315   0.04579  -0.0367   0.0584   1.0000
  12.500   1.4282   0.05666   0.04930  -0.0361   0.0568   1.0000
  12.750   1.4280   0.05954   0.05228  -0.0356   0.0553   1.0000
  13.000   1.4280   0.06244   0.05530  -0.0353   0.0538   1.0000
  13.250   1.4278   0.06536   0.05829  -0.0350   0.0522   1.0000
  13.500   1.4281   0.06819   0.06115  -0.0346   0.0508   1.0000
  13.750   1.4322   0.07016   0.06302  -0.0332   0.0491   1.0000
  14.000   1.4355   0.07268   0.06566  -0.0326   0.0479   1.0000
  14.250   1.4378   0.07546   0.06858  -0.0325   0.0468   1.0000
  14.500   1.4401   0.07824   0.07147  -0.0323   0.0456   1.0000
  14.750   1.4433   0.08083   0.07413  -0.0321   0.0444   1.0000
  15.000   1.4495   0.08291   0.07621  -0.0315   0.0432   1.0000
  15.250   1.4643   0.08369   0.07692  -0.0291   0.0416   1.0000
  15.500   1.4593   0.08766   0.08111  -0.0301   0.0410   1.0000
  15.750   1.4553   0.09155   0.08520  -0.0310   0.0404   1.0000
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