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

GOE 493 AIRFOIL (goe493-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 493 AIRFOIL (goe493-il)
Reynolds number: 200,000
Max Cl/Cd: 72.89 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe493-il-200000-n5.txt
Download as CSV file: xf-goe493-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 493 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.750  -0.5729   0.11031   0.10615  -0.0628   1.0000   0.0187
 -15.500  -0.6252   0.09596   0.09158  -0.0701   1.0000   0.0185
 -15.250  -0.6546   0.08709   0.08256  -0.0745   1.0000   0.0183
 -15.000  -0.6757   0.08020   0.07554  -0.0779   1.0000   0.0183
 -14.750  -0.6947   0.07417   0.06940  -0.0807   1.0000   0.0183
 -14.500  -0.7119   0.06875   0.06387  -0.0831   1.0000   0.0185
 -14.250  -0.7283   0.06384   0.05886  -0.0850   1.0000   0.0186
 -14.000  -0.7437   0.05942   0.05435  -0.0864   1.0000   0.0186
 -13.750  -0.7590   0.05541   0.05024  -0.0873   1.0000   0.0188
 -13.500  -0.7743   0.05187   0.04662  -0.0875   1.0000   0.0189
 -13.250  -0.7912   0.04872   0.04338  -0.0870   1.0000   0.0191
 -13.000  -0.8096   0.04594   0.04053  -0.0856   1.0000   0.0192
 -12.750  -0.8038   0.04226   0.03666  -0.0897   0.9963   0.0197
 -12.500  -0.7942   0.03906   0.03327  -0.0936   0.9911   0.0203
 -12.250  -0.7827   0.03629   0.03027  -0.0969   0.9859   0.0208
 -12.000  -0.7748   0.03378   0.02768  -0.0993   0.9794   0.0213
 -11.750  -0.7621   0.03178   0.02556  -0.1013   0.9739   0.0219
 -11.500  -0.7536   0.03032   0.02399  -0.1010   0.9664   0.0226
 -11.250  -0.7358   0.02890   0.02241  -0.1018   0.9618   0.0237
 -11.000  -0.7203   0.02769   0.02104  -0.1015   0.9557   0.0250
 -10.750  -0.7026   0.02637   0.01962  -0.1018   0.9505   0.0262
 -10.500  -0.6778   0.02519   0.01835  -0.1030   0.9475   0.0280
 -10.250  -0.6602   0.02425   0.01728  -0.1023   0.9419   0.0299
 -10.000  -0.6399   0.02324   0.01617  -0.1022   0.9367   0.0319
  -9.750  -0.6134   0.02230   0.01514  -0.1031   0.9336   0.0350
  -9.500  -0.5852   0.02133   0.01411  -0.1043   0.9312   0.0392
  -9.250  -0.5701   0.02075   0.01344  -0.1025   0.9237   0.0431
  -9.000  -0.5453   0.01997   0.01263  -0.1028   0.9196   0.0489
  -8.750  -0.5164   0.01926   0.01189  -0.1037   0.9167   0.0566
  -8.500  -0.4927   0.01873   0.01133  -0.1034   0.9120   0.0646
  -8.250  -0.4707   0.01831   0.01087  -0.1027   0.9062   0.0729
  -8.000  -0.4421   0.01786   0.01035  -0.1032   0.9025   0.0826
  -7.750  -0.4115   0.01739   0.00986  -0.1042   0.8996   0.0922
  -7.500  -0.3916   0.01709   0.00952  -0.1029   0.8932   0.1000
  -7.250  -0.3651   0.01678   0.00913  -0.1029   0.8884   0.1094
  -7.000  -0.3362   0.01634   0.00868  -0.1034   0.8848   0.1180
  -6.750  -0.3111   0.01605   0.00831  -0.1030   0.8798   0.1256
  -6.500  -0.2887   0.01572   0.00799  -0.1022   0.8738   0.1336
  -6.250  -0.2603   0.01538   0.00758  -0.1025   0.8697   0.1426
  -6.000  -0.2331   0.01506   0.00723  -0.1026   0.8654   0.1524
  -5.750  -0.2118   0.01479   0.00698  -0.1014   0.8586   0.1619
  -5.500  -0.1843   0.01448   0.00664  -0.1015   0.8541   0.1736
  -5.250  -0.1567   0.01419   0.00632  -0.1016   0.8497   0.1869
  -5.000  -0.1352   0.01396   0.00611  -0.1005   0.8430   0.2002
  -4.750  -0.1081   0.01366   0.00582  -0.1004   0.8381   0.2177
  -4.500  -0.0818   0.01337   0.00556  -0.1003   0.8333   0.2371
  -4.250  -0.0593   0.01315   0.00540  -0.0993   0.8265   0.2576
  -4.000  -0.0319   0.01289   0.00517  -0.0993   0.8217   0.2837
  -3.750  -0.0073   0.01267   0.00502  -0.0988   0.8158   0.3117
  -3.500   0.0168   0.01248   0.00490  -0.0981   0.8094   0.3386
  -3.250   0.0453   0.01229   0.00473  -0.0982   0.8048   0.3664
  -3.000   0.0686   0.01217   0.00467  -0.0973   0.7979   0.3925
  -2.750   0.0947   0.01204   0.00457  -0.0970   0.7918   0.4173
  -2.500   0.1229   0.01193   0.00446  -0.0970   0.7867   0.4399
  -2.250   0.1465   0.01188   0.00443  -0.0961   0.7794   0.4601
  -2.000   0.1746   0.01178   0.00433  -0.0961   0.7739   0.4800
  -1.750   0.1994   0.01173   0.00431  -0.0955   0.7670   0.4994
  -1.500   0.2256   0.01167   0.00427  -0.0951   0.7604   0.5187
  -1.250   0.2532   0.01160   0.00421  -0.0950   0.7549   0.5384
  -1.000   0.2773   0.01158   0.00422  -0.0942   0.7472   0.5551
  -0.750   0.3056   0.01152   0.00415  -0.0941   0.7414   0.5714
  -0.500   0.3297   0.01150   0.00417  -0.0934   0.7339   0.5870
  -0.250   0.3565   0.01146   0.00415  -0.0931   0.7275   0.6030
   0.000   0.3820   0.01143   0.00416  -0.0925   0.7206   0.6203
   0.250   0.4073   0.01140   0.00416  -0.0919   0.7127   0.6383
   0.500   0.4325   0.01137   0.00417  -0.0913   0.7046   0.6569
   0.750   0.4577   0.01134   0.00417  -0.0906   0.6955   0.6757
   1.000   0.4815   0.01133   0.00421  -0.0897   0.6858   0.6954
   1.250   0.5072   0.01131   0.00420  -0.0891   0.6768   0.7160
   1.500   0.5301   0.01132   0.00428  -0.0880   0.6670   0.7381
   1.750   0.5552   0.01133   0.00432  -0.0873   0.6593   0.7620
   2.000   0.5791   0.01135   0.00441  -0.0864   0.6513   0.7862
   2.250   0.6054   0.01137   0.00448  -0.0860   0.6446   0.8124
   2.500   0.6314   0.01140   0.00461  -0.0855   0.6368   0.8406
   2.750   0.6638   0.01145   0.00470  -0.0863   0.6297   0.8720
   3.000   0.7013   0.01154   0.00488  -0.0884   0.6209   0.9067
   3.250   0.7477   0.01167   0.00502  -0.0924   0.6132   0.9407
   3.500   0.7909   0.01180   0.00520  -0.0959   0.6047   0.9763
   3.750   0.8292   0.01199   0.00535  -0.0983   0.5971   1.0000
   4.000   0.8481   0.01213   0.00551  -0.0966   0.5888   1.0000
   4.250   0.8693   0.01229   0.00563  -0.0954   0.5812   1.0000
   4.500   0.8887   0.01245   0.00581  -0.0938   0.5723   1.0000
   4.750   0.9097   0.01263   0.00597  -0.0925   0.5640   1.0000
   5.000   0.9288   0.01281   0.00615  -0.0908   0.5536   1.0000
   5.250   0.9464   0.01300   0.00633  -0.0888   0.5403   1.0000
   5.500   0.9629   0.01321   0.00651  -0.0866   0.5249   1.0000
   5.750   0.9780   0.01344   0.00669  -0.0842   0.5077   1.0000
   6.000   0.9925   0.01370   0.00690  -0.0816   0.4902   1.0000
   6.250   1.0059   0.01397   0.00712  -0.0788   0.4726   1.0000
   6.500   1.0171   0.01427   0.00738  -0.0757   0.4544   1.0000
   6.750   1.0279   0.01461   0.00767  -0.0725   0.4337   1.0000
   7.000   1.0362   0.01505   0.00800  -0.0690   0.4098   1.0000
   7.250   1.0422   0.01560   0.00842  -0.0653   0.3812   1.0000
   7.500   1.0494   0.01621   0.00891  -0.0619   0.3571   1.0000
   7.750   1.0567   0.01689   0.00948  -0.0586   0.3335   1.0000
   8.000   1.0644   0.01761   0.01011  -0.0556   0.3117   1.0000
   8.250   1.0741   0.01831   0.01076  -0.0530   0.2904   1.0000
   8.500   1.0818   0.01913   0.01149  -0.0502   0.2653   1.0000
   8.750   1.0862   0.02016   0.01237  -0.0471   0.2264   1.0000
   9.000   1.0797   0.02183   0.01368  -0.0429   0.1710   1.0000
   9.250   1.0792   0.02336   0.01502  -0.0397   0.1388   1.0000
   9.500   1.0819   0.02478   0.01632  -0.0370   0.1096   1.0000
   9.750   1.0831   0.02636   0.01774  -0.0344   0.0847   1.0000
  10.000   1.0868   0.02783   0.01914  -0.0321   0.0712   1.0000
  10.250   1.0934   0.02917   0.02049  -0.0302   0.0622   1.0000
  10.500   1.1003   0.03053   0.02187  -0.0285   0.0569   1.0000
  10.750   1.1072   0.03193   0.02332  -0.0269   0.0529   1.0000
  11.000   1.1124   0.03350   0.02491  -0.0252   0.0500   1.0000
  11.250   1.1198   0.03495   0.02644  -0.0238   0.0477   1.0000
  11.500   1.1263   0.03652   0.02808  -0.0225   0.0456   1.0000
  11.750   1.1317   0.03822   0.02984  -0.0212   0.0440   1.0000
  12.000   1.1347   0.04018   0.03185  -0.0199   0.0425   1.0000
  12.250   1.1386   0.04214   0.03386  -0.0188   0.0413   1.0000
  12.500   1.1444   0.04397   0.03581  -0.0179   0.0401   1.0000
  12.750   1.1501   0.04587   0.03779  -0.0170   0.0387   1.0000
  13.000   1.1543   0.04793   0.03994  -0.0162   0.0377   1.0000
  13.250   1.1583   0.05008   0.04215  -0.0155   0.0366   1.0000
  13.500   1.1606   0.05245   0.04456  -0.0149   0.0356   1.0000
  13.750   1.1610   0.05503   0.04716  -0.0142   0.0345   1.0000
  14.000   1.1673   0.05708   0.04933  -0.0138   0.0337   1.0000
  14.250   1.1727   0.05924   0.05161  -0.0134   0.0328   1.0000
  14.500   1.1777   0.06149   0.05395  -0.0130   0.0319   1.0000
  14.750   1.1824   0.06381   0.05635  -0.0128   0.0308   1.0000
  15.000   1.1863   0.06622   0.05882  -0.0127   0.0299   1.0000
  15.250   1.1896   0.06872   0.06137  -0.0125   0.0291   1.0000
  15.500   1.1930   0.07115   0.06379  -0.0122   0.0283   1.0000
  15.750   1.1983   0.07355   0.06634  -0.0122   0.0276   1.0000
  16.000   1.2027   0.07609   0.06903  -0.0123   0.0268   1.0000
  16.250   1.2065   0.07870   0.07177  -0.0124   0.0260   1.0000
  16.500   1.2096   0.08145   0.07462  -0.0127   0.0251   1.0000
  16.750   1.2119   0.08434   0.07758  -0.0132   0.0243   1.0000
  17.000   1.2149   0.08711   0.08041  -0.0136   0.0238   1.0000
  17.250   1.2177   0.08987   0.08320  -0.0139   0.0232   1.0000
  17.500   1.2192   0.09298   0.08645  -0.0145   0.0226   1.0000
  17.750   1.2190   0.09642   0.09008  -0.0153   0.0220   1.0000
  18.000   1.2183   0.09998   0.09381  -0.0163   0.0214   1.0000
  18.250   1.2166   0.10376   0.09774  -0.0176   0.0207   1.0000
  18.500   1.2152   0.10751   0.10163  -0.0189   0.0202   1.0000
<< Back to GOE 493 AIRFOIL (goe493-il)

Polar data table (+)

Polar graphs


<< Back to GOE 493 AIRFOIL (goe493-il)