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

GOE 434 AIRFOIL (goe434-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 434 AIRFOIL (goe434-il)
Reynolds number: 200,000
Max Cl/Cd: 65.26 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe434-il-200000.txt
Download as CSV file: xf-goe434-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 434 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.7248   0.05909   0.05352  -0.1039   0.9938   0.0970
 -14.000  -0.7370   0.05178   0.04587  -0.1137   0.9856   0.0979
 -13.750  -0.7335   0.04616   0.03993  -0.1228   0.9778   0.0989
 -13.500  -0.7282   0.04161   0.03505  -0.1305   0.9646   0.0999
 -13.250  -0.6851   0.04078   0.03437  -0.1315   0.9600   0.1015
 -13.000  -0.6590   0.03953   0.03316  -0.1327   0.9458   0.1029
 -12.750  -0.6440   0.03774   0.03130  -0.1340   0.9278   0.1043
 -12.500  -0.6363   0.03582   0.02924  -0.1346   0.9071   0.1055
 -12.250  -0.6299   0.03399   0.02723  -0.1349   0.8865   0.1066
 -12.000  -0.6249   0.03234   0.02535  -0.1351   0.8672   0.1076
 -11.750  -0.6086   0.03121   0.02415  -0.1346   0.8521   0.1089
 -11.500  -0.5875   0.03052   0.02346  -0.1338   0.8394   0.1104
 -11.250  -0.5688   0.02967   0.02257  -0.1340   0.8255   0.1120
 -11.000  -0.5501   0.02869   0.02143  -0.1345   0.8146   0.1137
 -10.750  -0.5315   0.02772   0.02033  -0.1351   0.8031   0.1155
 -10.500  -0.5111   0.02685   0.01931  -0.1353   0.7941   0.1171
 -10.250  -0.4881   0.02626   0.01875  -0.1352   0.7865   0.1190
 -10.000  -0.4657   0.02565   0.01815  -0.1354   0.7785   0.1211
  -9.750  -0.4428   0.02501   0.01742  -0.1357   0.7716   0.1235
  -9.500  -0.4189   0.02438   0.01660  -0.1361   0.7656   0.1259
  -9.250  -0.3953   0.02382   0.01614  -0.1361   0.7598   0.1282
  -9.000  -0.3709   0.02332   0.01565  -0.1364   0.7536   0.1310
  -8.750  -0.3458   0.02281   0.01507  -0.1367   0.7481   0.1345
  -8.500  -0.3206   0.02228   0.01451  -0.1369   0.7435   0.1379
  -8.250  -0.2943   0.02188   0.01409  -0.1372   0.7392   0.1418
  -8.000  -0.2683   0.02147   0.01362  -0.1375   0.7350   0.1467
  -7.750  -0.2434   0.02093   0.01319  -0.1378   0.7303   0.1520
  -7.500  -0.2167   0.02049   0.01269  -0.1381   0.7257   0.1596
  -7.250  -0.1908   0.01989   0.01218  -0.1385   0.7217   0.1689
  -7.000  -0.1641   0.01931   0.01166  -0.1390   0.7181   0.1819
  -6.750  -0.1364   0.01889   0.01127  -0.1396   0.7145   0.1983
  -6.500  -0.1089   0.01864   0.01108  -0.1401   0.7108   0.2150
  -6.250  -0.0811   0.01852   0.01104  -0.1404   0.7069   0.2301
  -6.000  -0.0524   0.01852   0.01106  -0.1406   0.7031   0.2433
  -5.750  -0.0234   0.01856   0.01114  -0.1408   0.6992   0.2543
  -5.500   0.0063   0.01860   0.01113  -0.1411   0.6956   0.2651
  -5.250   0.0366   0.01873   0.01118  -0.1414   0.6923   0.2756
  -5.000   0.0664   0.01897   0.01139  -0.1416   0.6888   0.2841
  -4.750   0.0942   0.01912   0.01157  -0.1415   0.6854   0.2932
  -4.500   0.1221   0.01922   0.01169  -0.1415   0.6816   0.3015
  -4.250   0.1506   0.01942   0.01194  -0.1414   0.6777   0.3091
  -4.000   0.1803   0.01957   0.01196  -0.1416   0.6740   0.3180
  -3.750   0.2094   0.01961   0.01208  -0.1416   0.6708   0.3248
  -3.500   0.2395   0.01981   0.01226  -0.1417   0.6678   0.3319
  -3.250   0.2700   0.02013   0.01243  -0.1420   0.6645   0.3396
  -3.000   0.2965   0.02013   0.01252  -0.1418   0.6610   0.3457
  -2.750   0.3232   0.02032   0.01282  -0.1414   0.6571   0.3516
  -2.500   0.3511   0.02050   0.01301  -0.1413   0.6533   0.3585
  -2.250   0.3803   0.02065   0.01306  -0.1415   0.6497   0.3647
  -2.000   0.4095   0.02053   0.01295  -0.1416   0.6464   0.3702
  -1.750   0.4397   0.02061   0.01305  -0.1417   0.6431   0.3755
  -1.500   0.4700   0.02094   0.01331  -0.1419   0.6397   0.3817
  -1.250   0.4959   0.02111   0.01350  -0.1416   0.6360   0.3880
  -1.000   0.5221   0.02117   0.01359  -0.1414   0.6320   0.3936
  -0.750   0.5487   0.02126   0.01377  -0.1411   0.6279   0.3988
  -0.500   0.5773   0.02130   0.01383  -0.1410   0.6239   0.4039
  -0.250   0.6084   0.02123   0.01368  -0.1413   0.6200   0.4091
   0.000   0.6412   0.02128   0.01357  -0.1419   0.6159   0.4142
   0.250   0.6665   0.02133   0.01365  -0.1415   0.6108   0.4185
   0.500   0.6914   0.02129   0.01372  -0.1409   0.6055   0.4234
   0.750   0.7190   0.02130   0.01377  -0.1407   0.6009   0.4286
   1.000   0.7496   0.02122   0.01365  -0.1409   0.5968   0.4342
   1.250   0.7826   0.02115   0.01345  -0.1414   0.5929   0.4399
   1.500   0.8107   0.02130   0.01355  -0.1414   0.5883   0.4445
   1.750   0.8336   0.02126   0.01366  -0.1406   0.5827   0.4496
   2.000   0.8604   0.02124   0.01369  -0.1403   0.5777   0.4551
   2.250   0.8908   0.02112   0.01355  -0.1404   0.5733   0.4613
   2.500   0.9240   0.02100   0.01331  -0.1410   0.5695   0.4673
   2.750   0.9512   0.02105   0.01335  -0.1409   0.5646   0.4725
   3.000   0.9735   0.02099   0.01344  -0.1399   0.5582   0.4781
   3.250   1.0018   0.02083   0.01328  -0.1397   0.5528   0.4845
   3.500   1.0339   0.02062   0.01300  -0.1401   0.5484   0.4922
   3.750   1.0640   0.02063   0.01295  -0.1403   0.5443   0.5000
   4.000   1.0838   0.02074   0.01326  -0.1389   0.5382   0.5076
   4.250   1.1100   0.02071   0.01327  -0.1385   0.5328   0.5169
   4.500   1.1406   0.02053   0.01302  -0.1387   0.5281   0.5271
   4.750   1.1682   0.02046   0.01301  -0.1384   0.5232   0.5370
   5.000   1.1877   0.02060   0.01326  -0.1370   0.5163   0.5483
   5.250   1.2137   0.02046   0.01317  -0.1364   0.5104   0.5598
   5.500   1.2448   0.02030   0.01293  -0.1367   0.5055   0.5745
   5.750   1.2597   0.02051   0.01336  -0.1345   0.4978   0.5868
   6.000   1.2830   0.02049   0.01334  -0.1336   0.4910   0.6031
   6.250   1.3059   0.02046   0.01337  -0.1326   0.4841   0.6184
   6.500   1.3212   0.02061   0.01364  -0.1305   0.4753   0.6341
   6.750   1.3436   0.02059   0.01357  -0.1293   0.4672   0.6525
   7.000   1.3515   0.02084   0.01397  -0.1260   0.4569   0.6680
   7.250   1.3663   0.02105   0.01420  -0.1238   0.4467   0.6861
   7.500   1.3777   0.02146   0.01462  -0.1213   0.4348   0.7055
   7.750   1.3865   0.02205   0.01526  -0.1186   0.4220   0.7260
   8.000   1.3947   0.02270   0.01592  -0.1159   0.4088   0.7472
   8.250   1.4006   0.02351   0.01671  -0.1131   0.3941   0.7699
   8.500   1.4022   0.02461   0.01782  -0.1101   0.3777   0.7943
   8.750   1.4013   0.02592   0.01916  -0.1070   0.3602   0.8251
   9.000   1.3960   0.02724   0.02058  -0.1033   0.3431   0.8943
   9.250   1.3921   0.02904   0.02229  -0.1008   0.3264   1.0000
   9.500   1.3928   0.03107   0.02419  -0.0991   0.3117   1.0000
   9.750   1.3947   0.03305   0.02606  -0.0976   0.2997   1.0000
  10.000   1.3968   0.03503   0.02789  -0.0960   0.2900   1.0000
  10.250   1.4034   0.03678   0.02961  -0.0949   0.2814   1.0000
  10.500   1.4090   0.03855   0.03123  -0.0937   0.2746   1.0000
  10.750   1.4186   0.04008   0.03275  -0.0927   0.2687   1.0000
  11.000   1.4282   0.04161   0.03425  -0.0918   0.2634   1.0000
  11.250   1.4400   0.04291   0.03542  -0.0908   0.2589   1.0000
  11.500   1.4538   0.04408   0.03655  -0.0900   0.2549   1.0000
  11.750   1.4652   0.04551   0.03802  -0.0893   0.2511   1.0000
  12.000   1.4769   0.04690   0.03940  -0.0885   0.2474   1.0000
  12.250   1.4909   0.04803   0.04045  -0.0877   0.2438   1.0000
  12.500   1.5097   0.04871   0.04101  -0.0869   0.2400   1.0000
  12.750   1.5168   0.05058   0.04298  -0.0863   0.2369   1.0000
  13.000   1.5268   0.05217   0.04461  -0.0856   0.2336   1.0000
  13.250   1.5386   0.05357   0.04602  -0.0849   0.2306   1.0000
  13.500   1.5528   0.05470   0.04711  -0.0843   0.2276   1.0000
  13.750   1.5779   0.05478   0.04702  -0.0835   0.2241   1.0000
  14.000   1.5800   0.05715   0.04954  -0.0829   0.2217   1.0000
  14.250   1.5864   0.05913   0.05162  -0.0824   0.2190   1.0000
  14.500   1.5954   0.06082   0.05336  -0.0818   0.2163   1.0000
  14.750   1.6060   0.06235   0.05490  -0.0813   0.2137   1.0000
  15.000   1.6202   0.06348   0.05599  -0.0807   0.2110   1.0000
  15.250   1.6473   0.06333   0.05571  -0.0800   0.2080   1.0000
  15.500   1.6440   0.06631   0.05887  -0.0796   0.2059   1.0000
  15.750   1.6444   0.06894   0.06163  -0.0792   0.2034   1.0000
  16.000   1.6479   0.07126   0.06403  -0.0789   0.2006   1.0000
  16.250   1.6552   0.07314   0.06594  -0.0785   0.1979   1.0000
  16.500   1.6680   0.07438   0.06714  -0.0781   0.1952   1.0000
  16.750   1.6888   0.07475   0.06743  -0.0774   0.1921   1.0000
  17.000   1.6764   0.07890   0.07180  -0.0774   0.1897   1.0000
  17.250   1.6703   0.08242   0.07547  -0.0775   0.1866   1.0000
  17.500   1.6722   0.08499   0.07809  -0.0775   0.1834   1.0000
  17.750   1.6822   0.08652   0.07958  -0.0773   0.1804   1.0000
  18.000   1.6943   0.08777   0.08078  -0.0769   0.1771   1.0000
  18.250   1.6739   0.09325   0.08651  -0.0777   0.1739   1.0000
  18.500   1.6680   0.09696   0.09032  -0.0782   0.1702   1.0000
<< Back to GOE 434 AIRFOIL (goe434-il)

Polar data table (+)

Polar graphs


<< Back to GOE 434 AIRFOIL (goe434-il)