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GOE 63 AIRFOIL (goe63-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 63 AIRFOIL (goe63-il)
Reynolds number: 100,000
Max Cl/Cd: 60.97 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe63-il-100000.txt
Download as CSV file: xf-goe63-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 63 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2312   0.11025   0.10564  -0.0296   1.0000   0.0511
  -8.000  -0.2540   0.11114   0.10672  -0.0250   1.0000   0.0511
  -7.750  -0.2857   0.11258   0.10831  -0.0180   1.0000   0.0510
  -7.250  -0.2461   0.10447   0.10022  -0.0281   0.9872   0.0519
  -7.000  -0.2196   0.09930   0.09503  -0.0313   0.9828   0.0530
  -6.750  -0.1933   0.09530   0.09101  -0.0366   0.9741   0.0547
  -6.500  -0.1640   0.09157   0.08726  -0.0435   0.9664   0.0569
  -6.250  -0.1239   0.08872   0.08433  -0.0561   0.9574   0.0594
  -6.000  -0.0777   0.08654   0.08203  -0.0720   0.9462   0.0602
  -5.750  -0.0609   0.08055   0.07608  -0.0699   0.9427   0.0611
  -5.500  -0.0374   0.07673   0.07226  -0.0722   0.9360   0.0625
  -5.250  -0.0091   0.07346   0.06896  -0.0768   0.9283   0.0645
  -5.000   0.0276   0.07019   0.06561  -0.0838   0.9223   0.0674
  -4.750   0.0959   0.05220   0.04782  -0.0893   0.8904   0.0721
  -4.500   0.1049   0.05003   0.04566  -0.0886   0.8806   0.0739
  -4.250   0.1303   0.04695   0.04253  -0.0920   0.8753   0.0772
  -4.000   0.1810   0.04698   0.04218  -0.1048   0.8659   0.0820
  -3.750   0.1910   0.04236   0.03769  -0.1033   0.8607   0.0829
  -3.500   0.2089   0.03879   0.03415  -0.1029   0.8565   0.0849
  -3.250   0.2243   0.03724   0.03258  -0.1035   0.8478   0.0877
  -3.000   0.2779   0.03588   0.03083  -0.1125   0.8418   0.0950
  -2.750   0.2903   0.03247   0.02752  -0.1114   0.8354   0.0967
  -2.500   0.3108   0.03025   0.02529  -0.1116   0.8264   0.1005
  -2.250   0.3510   0.02817   0.02294  -0.1157   0.8186   0.1096
  -2.000   0.3695   0.02607   0.02086  -0.1152   0.8089   0.1147
  -1.750   0.4037   0.02403   0.01863  -0.1176   0.8023   0.1255
  -1.500   0.4345   0.02335   0.01774  -0.1197   0.7932   0.1385
  -1.250   0.4579   0.02097   0.01540  -0.1196   0.7877   0.1468
  -1.000   0.4832   0.01999   0.01436  -0.1206   0.7788   0.1612
  -0.750   0.5146   0.01868   0.01286  -0.1220   0.7719   0.1880
  -0.500   0.5377   0.01745   0.01165  -0.1220   0.7640   0.2097
   1.250   0.7937   0.02662   0.01909  -0.1344   0.7220   0.2319
   1.500   0.8302   0.02608   0.01798  -0.1333   0.7138   0.1498
   1.750   0.8599   0.02537   0.01704  -0.1325   0.7035   0.1292
   2.000   0.8885   0.02519   0.01658  -0.1314   0.6930   0.1219
   2.250   0.9176   0.02421   0.01551  -0.1306   0.6838   0.1184
   2.500   0.9438   0.02376   0.01501  -0.1296   0.6711   0.1152
   2.750   0.9712   0.02326   0.01443  -0.1286   0.6596   0.1145
   3.000   0.9991   0.02264   0.01369  -0.1274   0.6490   0.1185
   3.250   1.0242   0.02224   0.01326  -0.1261   0.6344   0.1254
   3.500   1.0504   0.02189   0.01287  -0.1251   0.6196   0.1337
   3.750   1.0773   0.02155   0.01247  -0.1241   0.6044   0.1541
   4.000   1.0985   0.01998   0.01215  -0.1220   0.5897   1.0000
   4.250   1.1248   0.01999   0.01180  -0.1208   0.5732   1.0000
   4.500   1.1505   0.02003   0.01167  -0.1199   0.5558   1.0000
   4.750   1.1759   0.02010   0.01160  -0.1190   0.5382   1.0000
   5.000   1.2012   0.02022   0.01158  -0.1182   0.5207   1.0000
   5.250   1.2263   0.02039   0.01164  -0.1173   0.5035   1.0000
   5.500   1.2511   0.02063   0.01175  -0.1165   0.4867   1.0000
   5.750   1.2756   0.02094   0.01193  -0.1158   0.4704   1.0000
   6.000   1.2998   0.02132   0.01221  -0.1150   0.4546   1.0000
   6.250   1.3236   0.02178   0.01258  -0.1142   0.4393   1.0000
   6.500   1.3473   0.02230   0.01300  -0.1134   0.4247   1.0000
   6.750   1.3708   0.02288   0.01349  -0.1127   0.4107   1.0000
   7.000   1.3942   0.02351   0.01402  -0.1119   0.3972   1.0000
   7.250   1.4182   0.02418   0.01453  -0.1113   0.3842   1.0000
   7.500   1.4398   0.02491   0.01528  -0.1104   0.3705   1.0000
   7.750   1.4614   0.02572   0.01609  -0.1095   0.3574   1.0000
   8.000   1.4833   0.02658   0.01694  -0.1087   0.3451   1.0000
   8.250   1.5065   0.02746   0.01769  -0.1081   0.3334   1.0000
   8.500   1.5268   0.02832   0.01858  -0.1071   0.3211   1.0000
   8.750   1.5461   0.02931   0.01967  -0.1059   0.3095   1.0000
   9.000   1.5683   0.03031   0.02059  -0.1052   0.2993   1.0000
   9.250   1.5873   0.03126   0.02162  -0.1041   0.2889   1.0000
   9.500   1.6056   0.03236   0.02282  -0.1029   0.2794   1.0000
   9.750   1.6277   0.03327   0.02366  -0.1022   0.2706   1.0000
  10.000   1.6419   0.03446   0.02508  -0.1005   0.2619   1.0000
  10.250   1.6649   0.03540   0.02592  -0.1000   0.2545   1.0000
  10.500   1.6781   0.03677   0.02756  -0.0982   0.2475   1.0000
  10.750   1.6970   0.03782   0.02868  -0.0972   0.2410   1.0000
  11.000   1.7154   0.03916   0.03008  -0.0962   0.2351   1.0000
  11.250   1.7257   0.04052   0.03170  -0.0941   0.2290   1.0000
  11.500   1.7508   0.04135   0.03238  -0.0940   0.2231   1.0000
  11.750   1.7552   0.04301   0.03438  -0.0913   0.2179   1.0000
  12.000   1.7643   0.04418   0.03573  -0.0891   0.2123   1.0000
  12.250   1.7862   0.04496   0.03638  -0.0886   0.2063   1.0000
  12.500   1.7805   0.04669   0.03848  -0.0848   0.2017   1.0000
  12.750   1.7868   0.04773   0.03961  -0.0824   0.1967   1.0000
  13.000   1.8055   0.04864   0.04045  -0.0816   0.1914   1.0000
  13.250   1.7911   0.05071   0.04286  -0.0770   0.1882   1.0000
  13.500   1.7853   0.05258   0.04495  -0.0740   0.1845   1.0000
  13.750   1.8098   0.05290   0.04512  -0.0737   0.1791   1.0000
  14.000   1.8018   0.05529   0.04777  -0.0709   0.1760   1.0000
  14.250   1.7838   0.05836   0.05117  -0.0680   0.1733   1.0000
  14.500   1.7734   0.06103   0.05405  -0.0661   0.1698   1.0000
  14.750   1.8022   0.06045   0.05323  -0.0657   0.1632   1.0000
  15.000   1.7764   0.06463   0.05779  -0.0637   0.1611   1.0000
  15.250   1.7531   0.06905   0.06253  -0.0625   0.1585   1.0000
  15.500   1.7398   0.07253   0.06619  -0.0619   0.1549   1.0000
  15.750   1.7591   0.07225   0.06575  -0.0611   0.1484   1.0000
  16.000   1.7294   0.07809   0.07195  -0.0611   0.1465   1.0000
  16.250   1.6997   0.08441   0.07858  -0.0619   0.1446   1.0000
  16.500   1.6703   0.09118   0.08560  -0.0633   0.1427   1.0000
  16.750   1.6092   0.10396   0.09873  -0.0676   0.1437   1.0000
  17.000   1.6027   0.10787   0.10274  -0.0689   0.1396   1.0000
  17.250   1.5687   0.11726   0.11230  -0.0730   0.1380   1.0000
  17.500   1.5313   0.12806   0.12323  -0.0783   0.1365   1.0000
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