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FX 77-W-270S (fx77w270s-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 77-W-270S (fx77w270s-il)
Reynolds number: 200,000
Max Cl/Cd: 10.3 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx77w270s-il-200000.txt
Download as CSV file: xf-fx77w270s-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 77-W-270S                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -19.500  -0.8214   0.11615   0.11130  -0.0408   1.0001   0.0361
 -19.250  -0.8596   0.10598   0.10079  -0.0470   1.0001   0.0362
 -19.000  -0.8399   0.10555   0.10053  -0.0469   1.0001   0.0368
 -18.750  -0.8403   0.10183   0.09679  -0.0490   1.0001   0.0372
 -18.500  -0.8458   0.09737   0.09225  -0.0514   1.0001   0.0377
 -18.250  -0.8553   0.09244   0.08720  -0.0538   1.0001   0.0381
 -18.000  -0.8656   0.08757   0.08219  -0.0560   1.0001   0.0385
 -17.750  -0.8762   0.08286   0.07731  -0.0579   1.0001   0.0388
 -17.500  -0.8850   0.07853   0.07281  -0.0593   1.0001   0.0391
 -17.250  -0.8918   0.07459   0.06872  -0.0605   1.0001   0.0394
 -17.000  -0.9011   0.07195   0.06531  -0.0598   0.7377   0.0396
 -16.750  -0.9065   0.06901   0.06181  -0.0598   0.6714   0.0399
 -16.500  -0.9097   0.06610   0.05852  -0.0600   0.6434   0.0402
 -16.250  -0.9054   0.06391   0.05607  -0.0600   0.6243   0.0406
 -16.000  -0.8912   0.06262   0.05470  -0.0599   0.6093   0.0410
 -15.750  -0.8804   0.06109   0.05307  -0.0598   0.5992   0.0415
 -15.500  -0.8712   0.05942   0.05129  -0.0597   0.5909   0.0419
 -15.250  -0.8623   0.05778   0.04949  -0.0596   0.5841   0.0424
 -15.000  -0.8527   0.05620   0.04774  -0.0594   0.5784   0.0428
 -14.750  -0.8432   0.05457   0.04601  -0.0591   0.5734   0.0434
 -14.500  -0.8329   0.05304   0.04433  -0.0588   0.5687   0.0439
 -14.250  -0.8218   0.05159   0.04271  -0.0585   0.5645   0.0444
 -14.000  -0.8109   0.05018   0.04109  -0.0580   0.5607   0.0448
 -13.750  -0.7931   0.04926   0.04012  -0.0577   0.5566   0.0454
 -13.500  -0.7767   0.04824   0.03914  -0.0575   0.5533   0.0461
 -13.250  -0.7621   0.04715   0.03804  -0.0572   0.5499   0.0469
 -13.000  -0.7478   0.04606   0.03687  -0.0568   0.5467   0.0478
 -12.750  -0.7324   0.04501   0.03572  -0.0564   0.5437   0.0486
 -12.500  -0.7164   0.04402   0.03460  -0.0560   0.5411   0.0493
 -12.250  -0.6988   0.04313   0.03360  -0.0555   0.5386   0.0499
 -12.000  -0.6788   0.04246   0.03293  -0.0552   0.5361   0.0506
 -11.750  -0.6605   0.04173   0.03220  -0.0548   0.5339   0.0514
 -11.500  -0.6425   0.04089   0.03138  -0.0544   0.5322   0.0522
 -11.250  -0.6245   0.04008   0.03055  -0.0539   0.5304   0.0531
 -11.000  -0.6066   0.03929   0.02971  -0.0535   0.5285   0.0541
 -10.750  -0.5887   0.03852   0.02888  -0.0530   0.5266   0.0553
 -10.500  -0.5717   0.03772   0.02814  -0.0525   0.5248   0.0564
 -10.250  -0.5545   0.03696   0.02738  -0.0520   0.5230   0.0578
 -10.000  -0.5371   0.03622   0.02661  -0.0514   0.5212   0.0594
  -9.750  -0.5200   0.03548   0.02581  -0.0508   0.5193   0.0611
  -9.500  -0.5044   0.03467   0.02503  -0.0502   0.5174   0.0628
  -9.250  -0.4878   0.03396   0.02428  -0.0495   0.5157   0.0649
  -9.000  -0.4714   0.03329   0.02356  -0.0489   0.5141   0.0673
  -8.750  -0.4566   0.03260   0.02292  -0.0482   0.5125   0.0699
  -8.500  -0.4400   0.03193   0.02223  -0.0475   0.5113   0.0736
  -8.250  -0.4270   0.03099   0.02137  -0.0466   0.5104   0.0775
  -8.000  -0.4138   0.03007   0.02051  -0.0457   0.5093   0.0828
  -7.750  -0.4016   0.02911   0.01961  -0.0447   0.5082   0.0902
  -7.500  -0.3918   0.02803   0.01864  -0.0435   0.5070   0.1002
  -7.250  -0.3838   0.02696   0.01768  -0.0420   0.5059   0.1143
  -7.000  -0.3806   0.02604   0.01687  -0.0394   0.5049   0.1309
  -6.750  -0.3833   0.02528   0.01623  -0.0355   0.5038   0.1493
  -6.500  -0.3833   0.02460   0.01570  -0.0318   0.5025   0.1747
  -6.250  -0.3797   0.02382   0.01514  -0.0286   0.5011   0.2128
  -6.000  -0.3765   0.02288   0.01453  -0.0255   0.4997   0.2690
  -5.750  -0.3733   0.02178   0.01391  -0.0223   0.4985   0.3549
  -5.500  -0.3664   0.02094   0.01383  -0.0191   0.4974   0.4748
  -5.250  -0.3385   0.02214   0.01554  -0.0177   0.4960   0.5595
  -5.000  -0.3106   0.02279   0.01608  -0.0176   0.4947   0.5931
  -4.750  -0.2822   0.02365   0.01681  -0.0174   0.4934   0.6125
  -4.500  -0.2514   0.02489   0.01801  -0.0171   0.4921   0.6255
  -4.250  -0.2206   0.02648   0.01958  -0.0166   0.4906   0.6368
  -4.000  -0.1937   0.02764   0.02071  -0.0161   0.4892   0.6514
  -3.750  -0.1589   0.02910   0.02231  -0.0155   0.4877   0.6575
  -3.500  -0.1294   0.02993   0.02316  -0.0151   0.4861   0.6647
  -3.250  -0.1061   0.03016   0.02333  -0.0149   0.4848   0.6732
  -3.000  -0.0758   0.03104   0.02427  -0.0145   0.4833   0.6769
  -2.750  -0.0465   0.03220   0.02547  -0.0137   0.4817   0.6856
  -2.500  -0.0192   0.03325   0.02655  -0.0126   0.4802   0.6962
  -2.250   0.0126   0.03442   0.02776  -0.0117   0.4786   0.7034
  -2.000   0.0297   0.03418   0.02741  -0.0113   0.4771   0.7138
  -1.750   0.0586   0.03439   0.02759  -0.0110   0.4755   0.7162
  -1.500   0.0866   0.03465   0.02780  -0.0107   0.4740   0.7196
  -1.250   0.1120   0.03491   0.02801  -0.0104   0.4728   0.7251
  -1.000   0.1301   0.03470   0.02767  -0.0108   0.4717   0.7338
  -0.750   0.1556   0.03494   0.02788  -0.0103   0.4705   0.7359
  -0.500   0.1790   0.03567   0.02858  -0.0098   0.4691   0.7384
  -0.250   0.1982   0.03632   0.02931  -0.0091   0.4678   0.7416
   0.000   0.2134   0.03685   0.02995  -0.0083   0.4659   0.7452
   0.250   0.2254   0.03757   0.03078  -0.0077   0.4631   0.7486
   0.500   0.2380   0.03848   0.03173  -0.0074   0.4605   0.7524
   0.750   0.2506   0.03942   0.03270  -0.0071   0.4583   0.7548
   1.000   0.2634   0.04015   0.03347  -0.0060   0.4563   0.7564
   1.250   0.2809   0.04072   0.03404  -0.0054   0.4547   0.7579
   1.500   0.3028   0.04106   0.03435  -0.0052   0.4534   0.7597
   1.750   0.3301   0.04109   0.03433  -0.0055   0.4523   0.7617
   2.000   0.3622   0.04088   0.03403  -0.0064   0.4514   0.7636
   2.250   0.3939   0.04079   0.03384  -0.0074   0.4504   0.7652
   2.500   0.4232   0.04107   0.03403  -0.0083   0.4492   0.7672
   3.500   0.1581   0.07459   0.06833   0.0042   0.4296   0.7742
   3.750   0.1779   0.07660   0.07030   0.0033   0.4292   0.7748
   4.000   0.1993   0.07870   0.07237   0.0024   0.4289   0.7754
   4.750   0.0843   0.09424   0.08814   0.0026   0.4183   0.7783
   5.000   0.1057   0.09535   0.08922   0.0021   0.4157   0.7792
   5.250   0.1312   0.09645   0.09028   0.0014   0.4141   0.7799
   5.500   0.1597   0.09756   0.09135   0.0005   0.4128   0.7806
   5.750   0.1911   0.09870   0.09246  -0.0004   0.4119   0.7813
   6.000   0.2252   0.09991   0.09363  -0.0013   0.4112   0.7821
   6.250   0.2619   0.10125   0.09493  -0.0022   0.4106   0.7828
   6.500   0.2946   0.10356   0.09721  -0.0031   0.4100   0.7837
   6.750   0.2069   0.10733   0.10110  -0.0019   0.3963   0.7842
   7.000   0.2348   0.10854   0.10229  -0.0026   0.3951   0.7855
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