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FX 77-W-270 (fx77w270-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 77-W-270 (fx77w270-il)
Reynolds number: 100,000
Max Cl/Cd: 12.84 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx77w270-il-100000-n5.txt
Download as CSV file: xf-fx77w270-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 77-W-270                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.250  -0.7544   0.12138   0.11449  -0.0174   0.6263   0.0377
 -17.000  -0.7932   0.10976   0.10249  -0.0245   0.6263   0.0376
 -16.750  -0.8121   0.10251   0.09494  -0.0284   0.6197   0.0376
 -16.500  -0.8243   0.09672   0.08889  -0.0312   0.6113   0.0378
 -16.000  -0.8376   0.08751   0.07918  -0.0348   0.5961   0.0382
 -15.750  -0.8405   0.08368   0.07511  -0.0360   0.5894   0.0385
 -15.500  -0.8412   0.08024   0.07143  -0.0368   0.5835   0.0387
 -15.250  -0.8405   0.07706   0.06802  -0.0375   0.5781   0.0391
 -15.000  -0.8378   0.07418   0.06492  -0.0379   0.5727   0.0394
 -14.750  -0.8338   0.07151   0.06202  -0.0381   0.5679   0.0398
 -14.500  -0.8256   0.06945   0.05985  -0.0382   0.5633   0.0401
 -14.250  -0.8168   0.06749   0.05781  -0.0382   0.5589   0.0405
 -14.000  -0.8077   0.06554   0.05580  -0.0382   0.5543   0.0409
 -13.750  -0.7983   0.06368   0.05384  -0.0381   0.5499   0.0413
 -13.500  -0.7886   0.06188   0.05192  -0.0379   0.5460   0.0418
 -13.250  -0.7782   0.06017   0.05007  -0.0377   0.5425   0.0423
 -13.000  -0.7669   0.05855   0.04831  -0.0374   0.5392   0.0429
 -12.750  -0.7546   0.05699   0.04664  -0.0370   0.5357   0.0436
 -12.500  -0.7432   0.05545   0.04507  -0.0367   0.5325   0.0442
 -12.250  -0.7321   0.05394   0.04351  -0.0364   0.5296   0.0449
 -12.000  -0.7202   0.05251   0.04201  -0.0361   0.5269   0.0458
 -11.750  -0.7075   0.05116   0.04057  -0.0357   0.5246   0.0468
 -11.500  -0.6943   0.04988   0.03918  -0.0353   0.5224   0.0480
 -11.000  -0.6679   0.04742   0.03663  -0.0346   0.5183   0.0505
 -10.750  -0.6528   0.04630   0.03545  -0.0342   0.5161   0.0522
 -10.500  -0.6386   0.04517   0.03431  -0.0338   0.5140   0.0539
 -10.250  -0.6228   0.04416   0.03321  -0.0334   0.5119   0.0561
 -10.000  -0.6076   0.04312   0.03212  -0.0329   0.5099   0.0583
  -9.750  -0.5915   0.04216   0.03106  -0.0324   0.5080   0.0612
  -9.500  -0.5772   0.04111   0.02997  -0.0317   0.5063   0.0637
  -9.250  -0.5619   0.04015   0.02891  -0.0310   0.5046   0.0669
  -9.000  -0.5502   0.03907   0.02782  -0.0299   0.5031   0.0696
  -8.750  -0.5396   0.03813   0.02682  -0.0286   0.5018   0.0726
  -8.500  -0.5319   0.03719   0.02585  -0.0269   0.5005   0.0754
  -8.250  -0.5186   0.03633   0.02499  -0.0261   0.4992   0.0790
  -8.000  -0.5021   0.03552   0.02423  -0.0257   0.4978   0.0835
  -7.750  -0.4834   0.03479   0.02353  -0.0256   0.4963   0.0894
  -7.500  -0.4629   0.03415   0.02289  -0.0256   0.4947   0.0979
  -7.250  -0.4423   0.03346   0.02225  -0.0256   0.4930   0.1079
  -7.000  -0.4214   0.03276   0.02169  -0.0258   0.4912   0.1200
  -6.750  -0.3981   0.03220   0.02121  -0.0261   0.4893   0.1410
  -6.500  -0.3749   0.03157   0.02071  -0.0265   0.4875   0.1631
  -6.250  -0.3503   0.03099   0.02026  -0.0271   0.4858   0.1987
  -6.000  -0.3259   0.03019   0.01973  -0.0281   0.4844   0.2462
  -5.750  -0.3004   0.02928   0.01918  -0.0296   0.4831   0.3145
  -5.500  -0.2757   0.02866   0.01927  -0.0301   0.4819   0.4176
  -5.250  -0.2528   0.03001   0.02113  -0.0266   0.4808   0.4945
  -5.000  -0.2263   0.03172   0.02295  -0.0238   0.4797   0.5281
  -4.750  -0.1931   0.03183   0.02295  -0.0261   0.4785   0.5638
  -4.500  -0.1610   0.03234   0.02340  -0.0274   0.4770   0.5833
  -4.000  -0.0981   0.03345   0.02436  -0.0294   0.4726   0.6127
  -3.750  -0.0678   0.03406   0.02489  -0.0299   0.4704   0.6248
  -3.500  -0.0346   0.03433   0.02500  -0.0320   0.4683   0.6392
  -3.250  -0.0092   0.03515   0.02581  -0.0303   0.4666   0.6438
  -3.000   0.0182   0.03581   0.02641  -0.0296   0.4651   0.6516
  -2.750   0.0480   0.03623   0.02673  -0.0303   0.4637   0.6623
  -2.500   0.0728   0.03695   0.02742  -0.0286   0.4626   0.6683
  -2.250   0.1040   0.03724   0.02758  -0.0300   0.4615   0.6791
  -2.000   0.1308   0.03758   0.02785  -0.0296   0.4604   0.6841
  -1.750   0.1574   0.03794   0.02813  -0.0291   0.4594   0.6878
  -1.500   0.1853   0.03833   0.02855  -0.0298   0.4580   0.6919
  -1.250   0.2152   0.03872   0.02896  -0.0316   0.4563   0.6971
  -1.000   0.2488   0.03904   0.02925  -0.0348   0.4545   0.7025
  -0.750   0.2753   0.03945   0.02968  -0.0354   0.4527   0.7041
  -0.500   0.3021   0.03986   0.03012  -0.0360   0.4509   0.7059
  -0.250   0.3291   0.04024   0.03049  -0.0366   0.4490   0.7080
   0.000   0.3567   0.04056   0.03079  -0.0374   0.4471   0.7103
   0.250   0.3852   0.04082   0.03101  -0.0384   0.4454   0.7130
   0.500   0.4147   0.04104   0.03117  -0.0397   0.4439   0.7160
   0.750   0.4456   0.04125   0.03130  -0.0413   0.4426   0.7192
   1.000   0.4781   0.04149   0.03145  -0.0434   0.4415   0.7223
   1.250   0.5100   0.04175   0.03162  -0.0453   0.4404   0.7247
   1.500   0.5376   0.04204   0.03186  -0.0458   0.4395   0.7262
   1.750   0.5561   0.04355   0.03354  -0.0465   0.4371   0.7276
   2.000   0.5612   0.04651   0.03682  -0.0467   0.4326   0.7290
   2.250   0.5678   0.04901   0.03949  -0.0467   0.4290   0.7304
   2.500   0.5796   0.05084   0.04139  -0.0468   0.4264   0.7318
   2.750   0.5965   0.05213   0.04270  -0.0471   0.4245   0.7333
   3.000   0.6161   0.05316   0.04372  -0.0476   0.4230   0.7348
   3.250   0.6399   0.05378   0.04432  -0.0482   0.4217   0.7364
   3.500   0.6672   0.05411   0.04460  -0.0490   0.4207   0.7387
   3.750   0.6971   0.05431   0.04473  -0.0501   0.4199   0.7413
   5.250   0.5386   0.08942   0.08049  -0.0486   0.3827   0.7484
   5.500   0.5565   0.09081   0.08188  -0.0490   0.3813   0.7494
   6.000   0.5148   0.10238   0.09365  -0.0503   0.3683   0.7513
   6.250   0.5361   0.10330   0.09456  -0.0508   0.3667   0.7526
   6.500   0.5594   0.10405   0.09528  -0.0513   0.3655   0.7539
   6.750   0.5839   0.10472   0.09594  -0.0520   0.3645   0.7549
   7.000   0.6087   0.10543   0.09663  -0.0526   0.3638   0.7559
   7.500   0.4058   0.11911   0.11107  -0.0340   0.3414   0.7535
   7.750   0.4052   0.12173   0.11374  -0.0341   0.3375   0.7543
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