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

GOE 435 AIRFOIL (goe435-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 435 AIRFOIL (goe435-il)
Reynolds number: 1,000,000
Max Cl/Cd: 95.18 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe435-il-1000000.txt
Download as CSV file: xf-goe435-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 435 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.750  -0.7275   0.09459   0.09071  -0.0689   0.9293   0.0622
 -17.500  -0.7233   0.09240   0.08842  -0.0691   0.9022   0.0623
 -17.250  -0.7190   0.09013   0.08600  -0.0696   0.8728   0.0624
 -17.000  -0.7152   0.08757   0.08329  -0.0705   0.8477   0.0625
 -16.750  -0.7104   0.08500   0.08060  -0.0716   0.8282   0.0626
 -16.500  -0.7054   0.08244   0.07794  -0.0728   0.8130   0.0627
 -16.250  -0.7024   0.07958   0.07498  -0.0742   0.8003   0.0628
 -16.000  -0.6975   0.07699   0.07231  -0.0754   0.7902   0.0628
 -15.750  -0.6946   0.07416   0.06941  -0.0767   0.7812   0.0630
 -15.500  -0.6952   0.07100   0.06615  -0.0782   0.7720   0.0632
 -15.250  -0.6966   0.06775   0.06284  -0.0798   0.7662   0.0635
 -15.000  -0.6990   0.06432   0.05935  -0.0814   0.7615   0.0637
 -14.750  -0.7020   0.06090   0.05586  -0.0831   0.7565   0.0639
 -14.500  -0.7036   0.05769   0.05257  -0.0846   0.7511   0.0642
 -14.250  -0.7063   0.05437   0.04915  -0.0863   0.7445   0.0644
 -14.000  -0.7058   0.05145   0.04619  -0.0877   0.7410   0.0646
 -13.750  -0.7074   0.04830   0.04299  -0.0894   0.7376   0.0648
 -13.500  -0.7057   0.04561   0.04025  -0.0907   0.7339   0.0651
 -13.250  -0.7062   0.04272   0.03728  -0.0922   0.7301   0.0653
 -13.000  -0.7040   0.04023   0.03473  -0.0935   0.7261   0.0656
 -12.750  -0.7026   0.03764   0.03206  -0.0948   0.7217   0.0658
 -12.500  -0.6990   0.03523   0.02958  -0.0962   0.7170   0.0660
 -12.250  -0.6936   0.03293   0.02724  -0.0975   0.7151   0.0663
 -12.000  -0.6870   0.03066   0.02493  -0.0989   0.7128   0.0666
 -11.750  -0.6787   0.02852   0.02275  -0.1003   0.7100   0.0669
 -11.500  -0.6684   0.02652   0.02070  -0.1018   0.7068   0.0672
 -11.250  -0.6560   0.02468   0.01879  -0.1033   0.7033   0.0676
 -11.000  -0.6427   0.02298   0.01703  -0.1047   0.6996   0.0679
 -10.750  -0.6295   0.02145   0.01542  -0.1061   0.6951   0.0683
 -10.500  -0.6085   0.02012   0.01403  -0.1082   0.6907   0.0686
 -10.250  -0.5842   0.01895   0.01283  -0.1105   0.6887   0.0690
 -10.000  -0.5580   0.01784   0.01167  -0.1129   0.6858   0.0695
  -9.750  -0.5310   0.01681   0.01060  -0.1152   0.6823   0.0707
  -9.500  -0.5042   0.01612   0.00987  -0.1164   0.6782   0.0718
  -9.250  -0.4769   0.01556   0.00928  -0.1173   0.6737   0.0729
  -9.000  -0.4492   0.01512   0.00879  -0.1181   0.6685   0.0741
  -8.750  -0.4206   0.01472   0.00836  -0.1189   0.6646   0.0753
  -8.500  -0.3918   0.01426   0.00790  -0.1196   0.6612   0.0774
  -8.250  -0.3635   0.01372   0.00737  -0.1204   0.6566   0.0811
  -8.000  -0.3386   0.01245   0.00634  -0.1219   0.6513   0.1304
  -7.750  -0.3086   0.01236   0.00628  -0.1223   0.6450   0.1397
  -7.500  -0.2777   0.01232   0.00625  -0.1227   0.6398   0.1441
  -7.250  -0.2468   0.01226   0.00618  -0.1231   0.6333   0.1468
  -7.000  -0.2167   0.01216   0.00607  -0.1235   0.6251   0.1494
  -6.750  -0.1862   0.01212   0.00603  -0.1239   0.6170   0.1514
  -6.500  -0.1558   0.01210   0.00598  -0.1242   0.6062   0.1530
  -6.250  -0.1257   0.01210   0.00592  -0.1246   0.5945   0.1544
  -5.750  -0.0659   0.01215   0.00585  -0.1251   0.5682   0.1561
  -5.500  -0.0362   0.01223   0.00585  -0.1253   0.5574   0.1566
  -5.250  -0.0069   0.01200   0.00558  -0.1258   0.5491   0.1584
  -5.000   0.0222   0.01191   0.00544  -0.1261   0.5402   0.1599
  -4.750   0.0523   0.01183   0.00535  -0.1265   0.5345   0.1611
  -4.500   0.0823   0.01178   0.00528  -0.1269   0.5288   0.1621
  -4.250   0.1119   0.01176   0.00522  -0.1272   0.5228   0.1630
  -4.000   0.1415   0.01175   0.00517  -0.1275   0.5168   0.1638
  -3.750   0.1722   0.01168   0.00510  -0.1279   0.5138   0.1646
  -3.500   0.2025   0.01162   0.00504  -0.1283   0.5104   0.1653
  -3.250   0.2326   0.01159   0.00499  -0.1287   0.5066   0.1661
  -3.000   0.2624   0.01159   0.00495  -0.1290   0.5023   0.1670
  -2.750   0.2917   0.01161   0.00493  -0.1292   0.4971   0.1676
  -2.500   0.3219   0.01159   0.00490  -0.1296   0.4941   0.1682
  -2.250   0.3525   0.01155   0.00487  -0.1300   0.4923   0.1687
  -2.000   0.3831   0.01152   0.00484  -0.1304   0.4902   0.1691
  -1.750   0.4134   0.01149   0.00482  -0.1308   0.4876   0.1693
  -1.500   0.4435   0.01138   0.00469  -0.1312   0.4847   0.1704
  -1.250   0.4734   0.01132   0.00460  -0.1316   0.4817   0.1717
  -1.000   0.5030   0.01128   0.00455  -0.1320   0.4785   0.1734
  -0.750   0.5322   0.01130   0.00454  -0.1322   0.4746   0.1750
  -0.500   0.5622   0.01128   0.00453  -0.1326   0.4721   0.1761
  -0.250   0.5928   0.01122   0.00449  -0.1330   0.4703   0.1773
   0.000   0.6232   0.01118   0.00447  -0.1334   0.4681   0.1786
   0.250   0.6534   0.01115   0.00446  -0.1338   0.4656   0.1797
   0.500   0.6832   0.01115   0.00446  -0.1341   0.4627   0.1807
   0.750   0.7125   0.01118   0.00446  -0.1343   0.4592   0.1816
   1.000   0.7411   0.01124   0.00449  -0.1344   0.4553   0.1824
   1.250   0.7694   0.01133   0.00456  -0.1345   0.4511   0.1832
   1.500   0.7996   0.01130   0.00455  -0.1348   0.4493   0.1844
   1.750   0.8297   0.01125   0.00454  -0.1352   0.4465   0.1875
   2.000   0.8593   0.01123   0.00455  -0.1355   0.4427   0.1913
   2.250   0.8879   0.01125   0.00457  -0.1356   0.4385   0.1952
   2.500   0.9155   0.01132   0.00463  -0.1356   0.4338   0.2014
   2.750   0.9446   0.01117   0.00463  -0.1361   0.4297   0.2424
   3.000   0.9753   0.01088   0.00468  -0.1369   0.4256   0.3479
   3.250   1.0033   0.01097   0.00480  -0.1369   0.4199   0.3621
   3.500   1.0291   0.01113   0.00494  -0.1366   0.4131   0.3701
   3.750   1.0569   0.01123   0.00507  -0.1365   0.4074   0.3771
   4.000   1.0826   0.01140   0.00521  -0.1362   0.3988   0.3816
   4.250   1.1069   0.01163   0.00538  -0.1356   0.3888   0.3842
   4.500   1.1280   0.01189   0.00559  -0.1345   0.3750   0.3898
   4.750   1.1444   0.01222   0.00586  -0.1326   0.3601   0.3937
   5.000   1.1615   0.01261   0.00619  -0.1309   0.3463   0.3968
   5.250   1.1806   0.01305   0.00657  -0.1296   0.3346   0.3996
   5.500   1.1982   0.01357   0.00703  -0.1282   0.3239   0.4020
   5.750   1.2188   0.01398   0.00741  -0.1272   0.3162   0.4040
   6.000   1.2357   0.01455   0.00793  -0.1258   0.3080   0.4055
   6.250   1.2572   0.01493   0.00830  -0.1251   0.3030   0.4076
   6.500   1.2766   0.01540   0.00878  -0.1242   0.2976   0.4116
   6.750   1.2937   0.01601   0.00936  -0.1230   0.2916   0.4151
   7.000   1.3138   0.01648   0.00986  -0.1222   0.2875   0.4185
   7.250   1.3337   0.01698   0.01037  -0.1214   0.2834   0.4221
   7.500   1.3512   0.01763   0.01101  -0.1204   0.2791   0.4250
   7.750   1.3664   0.01841   0.01178  -0.1192   0.2743   0.4271
   8.000   1.3853   0.01903   0.01241  -0.1185   0.2713   0.4288
   8.250   1.4050   0.01961   0.01301  -0.1179   0.2687   0.4301
   8.500   1.4236   0.02027   0.01369  -0.1172   0.2656   0.4339
   8.750   1.4395   0.02111   0.01455  -0.1164   0.2623   0.4381
   9.000   1.4538   0.02208   0.01553  -0.1154   0.2585   0.4418
   9.250   1.4682   0.02307   0.01655  -0.1145   0.2553   0.4453
   9.500   1.4876   0.02375   0.01726  -0.1141   0.2533   0.4490
   9.750   1.5040   0.02463   0.01818  -0.1134   0.2508   0.4526
  10.000   1.5189   0.02562   0.01918  -0.1127   0.2479   0.4554
  10.250   1.5312   0.02682   0.02041  -0.1118   0.2445   0.4622
  10.500   1.5405   0.02825   0.02186  -0.1108   0.2406   0.4692
  10.750   1.5563   0.02922   0.02289  -0.1102   0.2384   0.4770
  11.000   1.5712   0.03029   0.02401  -0.1096   0.2363   0.4869
  11.250   1.5857   0.03138   0.02518  -0.1090   0.2339   0.5020
  11.500   1.5975   0.03271   0.02658  -0.1084   0.2312   0.5238
  11.750   1.6069   0.03426   0.02822  -0.1076   0.2284   0.5562
  12.000   1.6147   0.03593   0.02997  -0.1068   0.2252   0.5933
  12.250   1.6271   0.03727   0.03146  -0.1063   0.2234   0.6337
  12.750   1.6534   0.03980   0.03420  -0.1052   0.2194   0.6965
  13.000   1.6611   0.04157   0.03604  -0.1045   0.2171   0.7191
  13.250   1.6683   0.04336   0.03788  -0.1037   0.2146   0.7376
  13.500   1.6716   0.04554   0.04011  -0.1028   0.2118   0.7516
  13.750   1.6782   0.04745   0.04206  -0.1021   0.2096   0.7647
  14.000   1.6906   0.04883   0.04352  -0.1016   0.2080   0.7783
  14.250   1.6984   0.05069   0.04545  -0.1011   0.2061   0.7902
  14.750   1.7105   0.05471   0.04958  -0.0999   0.2016   0.8169
  15.000   1.7119   0.05722   0.05216  -0.0993   0.1990   0.8351
  15.250   1.7093   0.05952   0.05472  -0.0979   0.1965   0.9747
  15.500   1.7187   0.06133   0.05657  -0.0977   0.1952   1.0000
  15.750   1.7274   0.06317   0.05844  -0.0974   0.1934   1.0000
  16.000   1.7314   0.06552   0.06083  -0.0970   0.1915   1.0000
  16.250   1.7356   0.06784   0.06318  -0.0966   0.1895   1.0000
  16.500   1.7362   0.07056   0.06592  -0.0963   0.1874   1.0000
  16.750   1.7351   0.07350   0.06887  -0.0960   0.1851   1.0000
  17.000   1.7390   0.07585   0.07125  -0.0957   0.1832   1.0000
  17.250   1.7440   0.07815   0.07361  -0.0956   0.1817   1.0000
  17.500   1.7497   0.08034   0.07583  -0.0954   0.1799   1.0000
  17.750   1.7543   0.08264   0.07816  -0.0953   0.1779   1.0000
  18.000   1.7527   0.08568   0.08123  -0.0952   0.1757   1.0000
  18.250   1.7518   0.08863   0.08419  -0.0951   0.1734   1.0000
<< Back to GOE 435 AIRFOIL (goe435-il)

Polar data table (+)

Polar graphs


<< Back to GOE 435 AIRFOIL (goe435-il)