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GOE 240 (KOLLER) AIRFOIL (goe240-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 240 (KOLLER) AIRFOIL (goe240-il)
Reynolds number: 500,000
Max Cl/Cd: 107.64 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe240-il-500000.txt
Download as CSV file: xf-goe240-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 240 (KOLLER) AIRFOIL                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3182   0.10184   0.09959  -0.0255   1.0000   0.0178
  -8.500  -0.3165   0.09929   0.09708  -0.0274   1.0000   0.0180
  -8.250  -0.3194   0.09710   0.09493  -0.0280   1.0000   0.0181
  -8.000  -0.2479   0.08062   0.07868  -0.0325   0.9977   0.0184
  -7.750  -0.2298   0.07630   0.07435  -0.0333   0.9960   0.0187
  -7.500  -0.2142   0.07222   0.07027  -0.0366   0.9932   0.0191
  -7.250  -0.3108   0.08433   0.08230  -0.0340   0.9957   0.0184
  -7.000  -0.2911   0.08067   0.07863  -0.0353   0.9939   0.0187
  -6.750  -0.2662   0.07689   0.07484  -0.0404   0.9897   0.0192
  -6.500  -0.2358   0.07278   0.07071  -0.0475   0.9860   0.0202
  -6.250  -0.1975   0.06781   0.06568  -0.0578   0.9827   0.0222
  -6.000  -0.1459   0.06144   0.05919  -0.0736   0.9741   0.0231
  -5.750  -0.1100   0.05625   0.05391  -0.0812   0.9669   0.0232
  -5.500  -0.0931   0.05110   0.04872  -0.0841   0.9574   0.0238
  -5.250  -0.0739   0.04884   0.04643  -0.0848   0.9441   0.0244
  -5.000  -0.0519   0.04646   0.04398  -0.0863   0.9286   0.0255
  -4.750  -0.0246   0.04326   0.04066  -0.0893   0.9108   0.0275
  -4.500   0.0199   0.03888   0.03594  -0.0947   0.8933   0.0296
  -4.250   0.0424   0.03312   0.02994  -0.0974   0.8775   0.0306
  -4.000   0.0648   0.03160   0.02830  -0.0977   0.8639   0.0315
  -3.750   0.0899   0.03005   0.02661  -0.0983   0.8525   0.0332
  -3.500   0.1255   0.02800   0.02415  -0.0992   0.8428   0.0380
  -3.250   0.1506   0.02359   0.01944  -0.1008   0.8338   0.0398
  -3.000   0.1759   0.02261   0.01835  -0.1010   0.8250   0.0414
  -2.750   0.2033   0.02142   0.01698  -0.1012   0.8160   0.0450
  -2.500   0.2318   0.01951   0.01474  -0.1015   0.8080   0.0509
  -2.250   0.2583   0.01877   0.01391  -0.1016   0.7999   0.0539
  -2.000   0.2872   0.01752   0.01234  -0.1016   0.7923   0.0619
  -1.750   0.3138   0.01675   0.01152  -0.1016   0.7843   0.0648
  -1.500   0.3437   0.01801   0.01254  -0.1009   0.7762   0.0722
  -1.250   0.3742   0.01184   0.00564  -0.1008   0.7704   0.0434
  -1.000   0.4024   0.01071   0.00429  -0.1004   0.7638   0.0409
  -0.750   0.4302   0.01020   0.00370  -0.1002   0.7566   0.0406
  -0.500   0.4579   0.00982   0.00326  -0.1000   0.7495   0.0407
  -0.250   0.4855   0.00950   0.00291  -0.0998   0.7408   0.0410
   0.000   0.5129   0.00925   0.00264  -0.0996   0.7305   0.0422
   0.250   0.5404   0.00905   0.00240  -0.0993   0.7196   0.0429
   0.500   0.5678   0.00889   0.00218  -0.0990   0.7070   0.0435
   0.750   0.5952   0.00876   0.00201  -0.0988   0.6928   0.0446
   1.000   0.6227   0.00867   0.00188  -0.0985   0.6776   0.0464
   1.250   0.6501   0.00862   0.00179  -0.0983   0.6607   0.0498
   1.500   0.6772   0.00859   0.00178  -0.0980   0.6373   0.0690
   1.750   0.7035   0.00865   0.00176  -0.0976   0.6060   0.0952
   2.000   0.7291   0.00863   0.00183  -0.0973   0.5726   0.1999
   2.250   0.7524   0.00720   0.00202  -0.0966   0.5489   1.0000
   2.500   0.7786   0.00744   0.00211  -0.0963   0.5285   1.0000
   2.750   0.8051   0.00765   0.00220  -0.0960   0.5111   1.0000
   3.000   0.8316   0.00785   0.00231  -0.0957   0.4947   1.0000
   3.250   0.8581   0.00804   0.00243  -0.0955   0.4776   1.0000
   3.500   0.8844   0.00825   0.00255  -0.0952   0.4589   1.0000
   3.750   0.9106   0.00846   0.00268  -0.0949   0.4376   1.0000
   4.000   0.9363   0.00874   0.00283  -0.0945   0.4085   1.0000
   4.250   0.9613   0.00908   0.00302  -0.0941   0.3765   1.0000
   4.500   0.9862   0.00943   0.00324  -0.0937   0.3500   1.0000
   4.750   1.0111   0.00979   0.00348  -0.0932   0.3266   1.0000
   5.000   1.0361   0.01013   0.00372  -0.0928   0.3058   1.0000
   5.250   1.0605   0.01054   0.00401  -0.0923   0.2795   1.0000
   5.500   1.0845   0.01098   0.00429  -0.0918   0.2459   1.0000
   5.750   1.1079   0.01149   0.00461  -0.0912   0.2104   1.0000
   6.000   1.1310   0.01202   0.00500  -0.0906   0.1821   1.0000
   6.250   1.1544   0.01250   0.00537  -0.0900   0.1636   1.0000
   6.500   1.1780   0.01295   0.00574  -0.0895   0.1481   1.0000
   6.750   1.2018   0.01335   0.00611  -0.0889   0.1368   1.0000
   7.000   1.2253   0.01378   0.00650  -0.0884   0.1244   1.0000
   7.250   1.2485   0.01422   0.00688  -0.0877   0.1081   1.0000
   7.500   1.2662   0.01526   0.00758  -0.0864   0.0606   1.0000
   7.750   1.2877   0.01586   0.00819  -0.0855   0.0496   1.0000
   8.000   1.3092   0.01645   0.00880  -0.0845   0.0383   1.0000
   8.250   1.3273   0.01738   0.00958  -0.0831   0.0200   1.0000
   8.500   1.3473   0.01807   0.01035  -0.0820   0.0177   1.0000
   8.750   1.3660   0.01888   0.01124  -0.0806   0.0162   1.0000
   9.000   1.3828   0.01982   0.01229  -0.0790   0.0151   1.0000
   9.250   1.3976   0.02088   0.01348  -0.0770   0.0144   1.0000
   9.500   1.4132   0.02178   0.01449  -0.0753   0.0140   1.0000
   9.750   1.4265   0.02280   0.01562  -0.0732   0.0136   1.0000
  10.000   1.4364   0.02386   0.01678  -0.0706   0.0131   1.0000
  10.250   1.4439   0.02500   0.01802  -0.0678   0.0126   1.0000
  10.500   1.4497   0.02630   0.01940  -0.0649   0.0121   1.0000
  10.750   1.4532   0.02780   0.02100  -0.0621   0.0117   1.0000
  11.000   1.4545   0.02957   0.02286  -0.0592   0.0114   1.0000
  11.250   1.4538   0.03161   0.02502  -0.0565   0.0112   1.0000
  11.500   1.4511   0.03402   0.02752  -0.0540   0.0110   1.0000
  11.750   1.4473   0.03676   0.03038  -0.0517   0.0108   1.0000
  12.000   1.4439   0.03973   0.03345  -0.0495   0.0106   1.0000
  12.250   1.4473   0.04197   0.03581  -0.0480   0.0105   1.0000
  12.500   1.4514   0.04412   0.03809  -0.0469   0.0104   1.0000
  12.750   1.4544   0.04647   0.04058  -0.0459   0.0102   1.0000
  13.000   1.4562   0.04901   0.04326  -0.0449   0.0101   1.0000
  13.250   1.4568   0.05176   0.04614  -0.0439   0.0100   1.0000
  13.500   1.4563   0.05471   0.04925  -0.0430   0.0100   1.0000
  13.750   1.4542   0.05788   0.05258  -0.0424   0.0099   1.0000
  14.000   1.4510   0.06127   0.05614  -0.0419   0.0098   1.0000
  14.250   1.4463   0.06491   0.05994  -0.0418   0.0097   1.0000
  14.500   1.4400   0.06886   0.06406  -0.0420   0.0096   1.0000
  14.750   1.4330   0.07306   0.06843  -0.0426   0.0095   1.0000
  15.000   1.4246   0.07764   0.07317  -0.0435   0.0094   1.0000
  15.250   1.4150   0.08257   0.07827  -0.0448   0.0093   1.0000
  15.500   1.4046   0.08784   0.08371  -0.0466   0.0092   1.0000
  15.750   1.3925   0.09362   0.08967  -0.0487   0.0092   1.0000
  16.000   1.3796   0.09972   0.09593  -0.0512   0.0092   1.0000
  16.250   1.3647   0.10639   0.10279  -0.0541   0.0093   1.0000
  16.500   1.3498   0.11338   0.10995  -0.0576   0.0093   1.0000
  16.750   1.3339   0.12084   0.11758  -0.0615   0.0094   1.0000
  17.000   1.3181   0.12857   0.12548  -0.0658   0.0095   1.0000
  17.250   1.3016   0.13676   0.13382  -0.0706   0.0096   1.0000
  17.500   1.2856   0.14525   0.14247  -0.0759   0.0097   1.0000
  17.750   1.2692   0.15423   0.15158  -0.0815   0.0098   1.0000
  18.000   1.2524   0.16367   0.16116  -0.0876   0.0099   1.0000
  18.250   1.2351   0.17376   0.17138  -0.0942   0.0101   1.0000
  18.500   1.2356   0.17746   0.17510  -0.0954   0.0108   1.0000
  18.750   1.2247   0.18723   0.18499  -0.1024   0.0109   1.0000
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