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FX 77-W-270 (fx77w270-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 77-W-270 (fx77w270-il)
Reynolds number: 50,000
Max Cl/Cd: 2.71 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx77w270-il-50000-n5.txt
Download as CSV file: xf-fx77w270-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.6602   0.10111   0.09250  -0.0396   0.6410   0.0721
 -14.250  -0.6969   0.09319   0.08424  -0.0428   0.6395   0.0721
 -14.000  -0.7223   0.08719   0.07795  -0.0444   0.6363   0.0723
 -13.750  -0.7216   0.08407   0.07469  -0.0449   0.6305   0.0730
 -13.500  -0.7247   0.08070   0.07111  -0.0452   0.6261   0.0737
 -13.250  -0.7287   0.07729   0.06746  -0.0454   0.6222   0.0745
 -13.000  -0.7311   0.07395   0.06391  -0.0455   0.6177   0.0753
 -12.750  -0.7320   0.07079   0.06048  -0.0454   0.6135   0.0763
 -12.500  -0.7307   0.06780   0.05718  -0.0451   0.6095   0.0773
 -12.250  -0.7189   0.06567   0.05485  -0.0448   0.6054   0.0784
 -12.000  -0.7001   0.06416   0.05324  -0.0447   0.6014   0.0797
 -11.750  -0.6815   0.06250   0.05148  -0.0447   0.5969   0.0813
 -11.500  -0.6623   0.06085   0.04962  -0.0445   0.5926   0.0831
 -11.250  -0.6387   0.05970   0.04840  -0.0443   0.5883   0.0851
 -11.000  -0.6148   0.05870   0.04729  -0.0441   0.5846   0.0874
 -10.750  -0.5897   0.05772   0.04608  -0.0437   0.5811   0.0904
 -10.500  -0.5631   0.05701   0.04543  -0.0438   0.5769   0.0935
 -10.250  -0.5377   0.05624   0.04455  -0.0437   0.5730   0.0979
 -10.000  -0.5158   0.05541   0.04369  -0.0435   0.5697   0.1032
  -9.750  -0.4958   0.05457   0.04288  -0.0431   0.5670   0.1088
  -9.500  -0.4771   0.05370   0.04202  -0.0427   0.5646   0.1151
  -9.250  -0.4599   0.05281   0.04113  -0.0421   0.5625   0.1224
  -9.000  -0.4428   0.05192   0.04025  -0.0417   0.5605   0.1309
  -8.750  -0.4247   0.05106   0.03947  -0.0413   0.5581   0.1410
  -8.500  -0.4086   0.05012   0.03866  -0.0408   0.5557   0.1520
  -8.250  -0.3961   0.04906   0.03779  -0.0400   0.5536   0.1639
  -8.000  -0.3868   0.04797   0.03685  -0.0388   0.5516   0.1800
  -7.750  -0.3808   0.04684   0.03587  -0.0373   0.5498   0.2007
  -7.500  -0.3806   0.04562   0.03491  -0.0350   0.5482   0.2237
  -7.250  -0.3778   0.04439   0.03391  -0.0333   0.5466   0.2595
  -7.000  -0.3736   0.04326   0.03320  -0.0314   0.5449   0.3095
  -6.750  -0.3530   0.04387   0.03446  -0.0287   0.5429   0.3834
  -6.500  -0.3076   0.04691   0.03777  -0.0266   0.5404   0.4513
  -6.250  -0.2815   0.04830   0.03918  -0.0258   0.5375   0.4911
  -6.000  -0.2624   0.04921   0.04004  -0.0249   0.5350   0.5230
  -5.750  -0.2420   0.05028   0.04099  -0.0240   0.5328   0.5508
  -5.500  -0.2255   0.05103   0.04162  -0.0232   0.5309   0.5769
  -5.250  -0.2088   0.05174   0.04220  -0.0225   0.5291   0.6003
  -5.000  -0.1882   0.05268   0.04299  -0.0217   0.5273   0.6198
  -4.750  -0.1586   0.05416   0.04434  -0.0205   0.5253   0.6339
  -4.500  -0.1315   0.05517   0.04521  -0.0193   0.5234   0.6475
  -4.250  -0.1120   0.05551   0.04537  -0.0183   0.5217   0.6627
  -4.000  -0.0839   0.05635   0.04608  -0.0177   0.5196   0.6726
  -3.750  -0.0672   0.05711   0.04686  -0.0179   0.5165   0.6846
  -3.500  -0.0433   0.05814   0.04788  -0.0179   0.5135   0.6937
  -3.250  -0.0283   0.05867   0.04835  -0.0175   0.5108   0.7054
  -3.000  -0.0039   0.05936   0.04896  -0.0172   0.5081   0.7128
  -2.750   0.0061   0.05937   0.04885  -0.0168   0.5059   0.7244
  -2.500   0.0317   0.05968   0.04906  -0.0163   0.5039   0.7291
  -2.250   0.0542   0.05987   0.04911  -0.0159   0.5022   0.7355
  -2.000   0.0698   0.05988   0.04898  -0.0156   0.5009   0.7441
  -1.750   0.0859   0.06061   0.04966  -0.0154   0.4991   0.7494
  -1.500   0.0789   0.06390   0.05320  -0.0151   0.4950   0.7540
  -1.250   0.0703   0.06659   0.05599  -0.0141   0.4912   0.7596
  -1.000   0.0686   0.06826   0.05766  -0.0135   0.4877   0.7660
  -0.750   0.0782   0.06918   0.05851  -0.0131   0.4850   0.7704
  -0.500   0.0945   0.06974   0.05899  -0.0124   0.4828   0.7737
  -0.250   0.1144   0.07010   0.05924  -0.0122   0.4812   0.7769
   0.000   0.1368   0.07039   0.05941  -0.0124   0.4799   0.7804
   0.500   0.0403   0.08099   0.07038  -0.0079   0.4711   0.7897
   0.750   0.0440   0.08275   0.07212  -0.0074   0.4684   0.7931
   1.000   0.0552   0.08401   0.07332  -0.0070   0.4658   0.7960
   1.250   0.0733   0.08499   0.07423  -0.0074   0.4635   0.7985
   1.500   0.0949   0.08588   0.07503  -0.0080   0.4617   0.8011
   1.750   0.1187   0.08680   0.07585  -0.0089   0.4603   0.8040
   2.000   0.1221   0.08919   0.07822  -0.0094   0.4575   0.8066
   2.250   0.1094   0.09252   0.08160  -0.0098   0.4527   0.8087
   2.500   0.1185   0.09458   0.08364  -0.0109   0.4496   0.8104
   2.750   0.1325   0.09651   0.08553  -0.0124   0.4473   0.8120
   3.000   0.1494   0.09804   0.08702  -0.0133   0.4450   0.8135
   3.250   0.1695   0.09919   0.08811  -0.0139   0.4428   0.8152
   3.500   0.1946   0.10012   0.08897  -0.0145   0.4408   0.8174
   3.750   0.2238   0.10091   0.08968  -0.0153   0.4392   0.8199
   4.000   0.2009   0.10485   0.09373  -0.0152   0.4339   0.8220
   4.250   0.2066   0.10726   0.09615  -0.0160   0.4314   0.8243
   4.500   0.2171   0.10948   0.09837  -0.0171   0.4293   0.8262
   4.750   0.2306   0.11162   0.10050  -0.0184   0.4273   0.8276
   5.000   0.2464   0.11369   0.10256  -0.0198   0.4255   0.8288
   5.250   0.2653   0.11561   0.10445  -0.0214   0.4237   0.8300
   5.500   0.2901   0.11722   0.10601  -0.0230   0.4216   0.8313
   5.750   0.3211   0.11862   0.10735  -0.0247   0.4199   0.8331
   6.000   0.3111   0.12184   0.11064  -0.0257   0.4151   0.8343
   6.250   0.3162   0.12430   0.11314  -0.0265   0.4128   0.8357
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