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

FX 77-W-270S (fx77w270s-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 77-W-270S (fx77w270s-il)
Reynolds number: 100,000
Max Cl/Cd: 9.02 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx77w270s-il-100000-n5.txt
Download as CSV file: xf-fx77w270s-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.250  -0.6323   0.11681   0.10987  -0.0410   0.6237   0.0435
 -17.000  -0.6930   0.10205   0.09471  -0.0497   0.6308   0.0432
 -16.750  -0.7183   0.09450   0.08683  -0.0535   0.6250   0.0434
 -16.500  -0.7349   0.08868   0.08071  -0.0560   0.6169   0.0436
 -16.250  -0.7463   0.08385   0.07560  -0.0578   0.6085   0.0439
 -16.000  -0.7539   0.07971   0.07118  -0.0590   0.6009   0.0442
 -15.750  -0.7584   0.07608   0.06728  -0.0599   0.5935   0.0445
 -15.500  -0.7599   0.07288   0.06382  -0.0604   0.5864   0.0448
 -15.000  -0.7485   0.06837   0.05904  -0.0608   0.5736   0.0455
 -14.750  -0.7414   0.06635   0.05691  -0.0609   0.5679   0.0459
 -14.500  -0.7334   0.06443   0.05485  -0.0609   0.5628   0.0463
 -14.250  -0.7249   0.06259   0.05286  -0.0608   0.5586   0.0468
 -14.000  -0.7155   0.06082   0.05097  -0.0606   0.5547   0.0473
 -13.750  -0.7053   0.05914   0.04918  -0.0604   0.5508   0.0479
 -13.500  -0.6943   0.05755   0.04745  -0.0602   0.5471   0.0486
 -13.250  -0.6826   0.05604   0.04578  -0.0598   0.5437   0.0494
 -13.000  -0.6702   0.05467   0.04431  -0.0595   0.5405   0.0502
 -12.750  -0.6578   0.05340   0.04297  -0.0591   0.5376   0.0510
 -12.500  -0.6450   0.05218   0.04165  -0.0588   0.5351   0.0519
 -12.250  -0.6310   0.05098   0.04038  -0.0584   0.5326   0.0529
 -12.000  -0.6159   0.04985   0.03915  -0.0580   0.5300   0.0541
 -11.750  -0.6006   0.04875   0.03799  -0.0576   0.5273   0.0554
 -11.500  -0.5868   0.04765   0.03687  -0.0572   0.5246   0.0566
 -11.250  -0.5720   0.04662   0.03579  -0.0568   0.5220   0.0582
 -11.000  -0.5561   0.04566   0.03473  -0.0563   0.5194   0.0600
 -10.750  -0.5410   0.04469   0.03372  -0.0558   0.5171   0.0618
 -10.500  -0.5261   0.04375   0.03273  -0.0553   0.5151   0.0637
 -10.250  -0.5099   0.04291   0.03178  -0.0547   0.5132   0.0662
 -10.000  -0.4947   0.04203   0.03088  -0.0542   0.5116   0.0684
  -9.750  -0.4790   0.04115   0.03001  -0.0536   0.5099   0.0712
  -9.500  -0.4629   0.04031   0.02915  -0.0530   0.5081   0.0742
  -9.250  -0.4481   0.03942   0.02829  -0.0523   0.5064   0.0775
  -9.000  -0.4326   0.03860   0.02745  -0.0516   0.5047   0.0815
  -8.750  -0.4181   0.03773   0.02661  -0.0508   0.5031   0.0861
  -8.500  -0.4038   0.03687   0.02578  -0.0500   0.5015   0.0918
  -8.250  -0.3892   0.03606   0.02498  -0.0492   0.4999   0.0991
  -8.000  -0.3748   0.03525   0.02420  -0.0483   0.4983   0.1081
  -7.750  -0.3609   0.03443   0.02342  -0.0473   0.4967   0.1190
  -7.500  -0.3477   0.03359   0.02266  -0.0462   0.4951   0.1328
  -7.250  -0.3349   0.03276   0.02190  -0.0451   0.4936   0.1507
  -7.000  -0.3234   0.03190   0.02114  -0.0438   0.4922   0.1733
  -6.500  -0.3146   0.02998   0.01951  -0.0393   0.4899   0.2347
  -6.250  -0.3229   0.02900   0.01880  -0.0349   0.4889   0.2710
  -6.000  -0.3288   0.02804   0.01817  -0.0307   0.4879   0.3236
  -5.750  -0.3300   0.02727   0.01793  -0.0266   0.4868   0.3966
  -5.500  -0.2764   0.03026   0.02183  -0.0260   0.4849   0.5104
  -5.250  -0.2534   0.03121   0.02281  -0.0245   0.4834   0.5481
  -5.000  -0.2474   0.03088   0.02238  -0.0221   0.4821   0.5754
  -4.500  -0.2185   0.03098   0.02220  -0.0190   0.4790   0.6108
  -4.250  -0.1860   0.03194   0.02310  -0.0188   0.4772   0.6175
  -4.000  -0.1704   0.03184   0.02284  -0.0176   0.4756   0.6312
  -3.750  -0.1347   0.03315   0.02411  -0.0173   0.4740   0.6389
  -3.500  -0.1120   0.03383   0.02469  -0.0160   0.4727   0.6536
  -3.250  -0.0766   0.03518   0.02599  -0.0155   0.4715   0.6632
  -3.000  -0.0583   0.03519   0.02587  -0.0144   0.4704   0.6736
  -2.750  -0.0284   0.03560   0.02618  -0.0144   0.4693   0.6770
  -2.500  -0.0029   0.03589   0.02642  -0.0142   0.4682   0.6816
  -2.250   0.0085   0.03566   0.02613  -0.0131   0.4667   0.6919
  -2.000   0.0339   0.03606   0.02658  -0.0127   0.4647   0.6945
  -1.750   0.0582   0.03639   0.02693  -0.0124   0.4627   0.6974
  -1.500   0.0808   0.03663   0.02716  -0.0120   0.4608   0.7009
  -1.250   0.1013   0.03679   0.02729  -0.0116   0.4592   0.7053
  -1.000   0.1194   0.03677   0.02720  -0.0113   0.4577   0.7104
  -0.750   0.1404   0.03688   0.02726  -0.0111   0.4563   0.7137
  -0.500   0.1638   0.03712   0.02747  -0.0108   0.4548   0.7158
  -0.250   0.1875   0.03728   0.02758  -0.0107   0.4534   0.7178
   0.000   0.2117   0.03738   0.02762  -0.0107   0.4521   0.7200
   0.250   0.2365   0.03746   0.02761  -0.0107   0.4508   0.7227
   0.500   0.2617   0.03752   0.02757  -0.0109   0.4497   0.7256
   0.750   0.2873   0.03761   0.02755  -0.0114   0.4486   0.7282
   1.000   0.2981   0.03856   0.02858  -0.0104   0.4464   0.7313
   1.250   0.2973   0.04021   0.03043  -0.0084   0.4433   0.7338
   1.500   0.2942   0.04199   0.03237  -0.0058   0.4399   0.7356
   1.750   0.2981   0.04328   0.03374  -0.0040   0.4369   0.7375
   2.000   0.3112   0.04404   0.03449  -0.0030   0.4348   0.7394
   2.250   0.3287   0.04457   0.03499  -0.0025   0.4331   0.7410
   2.500   0.3471   0.04511   0.03548  -0.0022   0.4317   0.7425
   2.750   0.3680   0.04556   0.03588  -0.0021   0.4306   0.7442
   3.000   0.3916   0.04592   0.03618  -0.0023   0.4296   0.7461
   3.250   0.4173   0.04625   0.03643  -0.0027   0.4288   0.7479
   5.750   0.2790   0.08435   0.07510   0.0023   0.3783   0.7605
   6.000   0.3017   0.08511   0.07582   0.0019   0.3773   0.7615
   6.250   0.3262   0.08568   0.07635   0.0014   0.3765   0.7625
   6.750   0.3060   0.09352   0.08429   0.0006   0.3648   0.7644
   7.000   0.3254   0.09462   0.08538   0.0001   0.3633   0.7654
   7.250   0.3475   0.09544   0.08617  -0.0004   0.3621   0.7668
   7.500   0.3719   0.09604   0.08674  -0.0008   0.3611   0.7683
   8.000   0.3595   0.10330   0.09410  -0.0020   0.3504   0.7707
   8.250   0.3781   0.10456   0.09534  -0.0026   0.3486   0.7719
   8.500   0.4001   0.10543   0.09619  -0.0032   0.3472   0.7730
   8.750   0.4242   0.10608   0.09681  -0.0037   0.3461   0.7741
   9.250   0.4159   0.11301   0.10383  -0.0050   0.3358   0.7758
   9.500   0.4337   0.11422   0.10506  -0.0055   0.3338   0.7769
<< Back to FX 77-W-270S (fx77w270s-il)

Polar data table (+)

Polar graphs


<< Back to FX 77-W-270S (fx77w270s-il)