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GOE 63 AIRFOIL (goe63-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 63 AIRFOIL (goe63-il)
Reynolds number: 200,000
Max Cl/Cd: 86.53 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe63-il-200000.txt
Download as CSV file: xf-goe63-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2145   0.10455   0.10116  -0.0286   1.0000   0.0319
  -8.250  -0.2136   0.10294   0.09964  -0.0290   1.0000   0.0324
  -8.000  -0.2092   0.10211   0.09889  -0.0338   0.9913   0.0328
  -7.750  -0.1830   0.09831   0.09508  -0.0435   0.9749   0.0330
  -7.500  -0.1611   0.09296   0.08973  -0.0437   0.9674   0.0333
  -7.250  -0.1384   0.08897   0.08572  -0.0474   0.9534   0.0337
  -7.000  -0.1174   0.08558   0.08229  -0.0513   0.9360   0.0343
  -6.750  -0.0995   0.08257   0.07924  -0.0546   0.9174   0.0350
  -6.500  -0.0836   0.07983   0.07644  -0.0574   0.8999   0.0357
  -6.250  -0.0674   0.07719   0.07372  -0.0603   0.8845   0.0365
  -6.000  -0.0460   0.07472   0.07115  -0.0653   0.8711   0.0375
  -5.750  -0.0079   0.07236   0.06862  -0.0780   0.8581   0.0381
  -5.500   0.0004   0.06892   0.06518  -0.0753   0.8482   0.0384
  -5.250   0.0151   0.06609   0.06229  -0.0753   0.8395   0.0389
  -5.000   0.0351   0.06347   0.05963  -0.0774   0.8300   0.0395
  -4.750   0.0581   0.06093   0.05700  -0.0802   0.8225   0.0404
  -4.500   0.0846   0.05835   0.05436  -0.0839   0.8144   0.0416
  -4.250   0.1203   0.05588   0.05175  -0.0899   0.8071   0.0434
  -4.000   0.1687   0.05317   0.04879  -0.0991   0.8004   0.0443
  -3.750   0.1836   0.05025   0.04590  -0.0985   0.7935   0.0448
  -3.500   0.2051   0.04792   0.04351  -0.0993   0.7874   0.0457
  -3.250   0.2327   0.04578   0.04132  -0.1016   0.7796   0.0476
  -3.000   0.2892   0.04463   0.03974  -0.1091   0.7721   0.0512
  -2.750   0.3147   0.04146   0.03651  -0.1108   0.7654   0.0518
  -2.500   0.3358   0.03901   0.03409  -0.1112   0.7578   0.0527
  -2.250   0.3623   0.03713   0.03209  -0.1122   0.7517   0.0541
  -2.000   0.3939   0.03538   0.03026  -0.1141   0.7434   0.0567
  -1.750   0.4388   0.03394   0.02838  -0.1174   0.7366   0.0606
  -1.500   0.4628   0.03173   0.02621  -0.1182   0.7305   0.0619
  -1.250   0.4915   0.03022   0.02465  -0.1192   0.7240   0.0646
  -1.000   0.5310   0.02930   0.02331  -0.1209   0.7186   0.0712
  -0.750   0.5567   0.02742   0.02150  -0.1218   0.7122   0.0736
  -0.500   0.5939   0.02822   0.02185  -0.1221   0.7055   0.0819
  -0.250   0.6211   0.02514   0.01881  -0.1235   0.7004   0.0842
   0.000   0.6499   0.02401   0.01768  -0.1242   0.6933   0.0888
   0.250   0.6821   0.02306   0.01649  -0.1248   0.6866   0.0974
   0.500   0.7133   0.02263   0.01580  -0.1251   0.6803   0.1093
   0.750   0.7415   0.02127   0.01452  -0.1258   0.6727   0.1163
   1.000   0.7713   0.02051   0.01359  -0.1261   0.6663   0.1321
   1.250   0.7997   0.01967   0.01274  -0.1266   0.6577   0.1603
   1.500   0.8278   0.01895   0.01194  -0.1269   0.6501   0.2053
   2.000   0.8949   0.01770   0.00994  -0.1252   0.6338   0.0919
   2.250   0.9246   0.01688   0.00896  -0.1248   0.6243   0.0761
   2.500   0.9536   0.01642   0.00826  -0.1242   0.6151   0.0713
   2.750   0.9811   0.01596   0.00787  -0.1240   0.6032   0.0746
   3.000   1.0088   0.01560   0.00747  -0.1236   0.5913   0.0759
   3.250   1.0364   0.01528   0.00710  -0.1231   0.5787   0.0774
   3.500   1.0637   0.01503   0.00685  -0.1227   0.5639   0.0806
   3.750   1.0908   0.01479   0.00665  -0.1224   0.5474   0.0891
   4.000   1.1177   0.01464   0.00648  -0.1221   0.5281   0.1033
   4.250   1.1367   0.01321   0.00633  -0.1199   0.5085   1.0000
   4.500   1.1621   0.01343   0.00633  -0.1193   0.4849   1.0000
   4.750   1.1871   0.01374   0.00644  -0.1187   0.4612   1.0000
   5.000   1.2116   0.01412   0.00664  -0.1181   0.4388   1.0000
   5.250   1.2358   0.01456   0.00692  -0.1174   0.4195   1.0000
   5.500   1.2599   0.01504   0.00724  -0.1168   0.4026   1.0000
   5.750   1.2841   0.01551   0.00760  -0.1163   0.3878   1.0000
   6.000   1.3082   0.01600   0.00801  -0.1157   0.3745   1.0000
   6.250   1.3320   0.01651   0.00843  -0.1151   0.3625   1.0000
   6.750   1.3791   0.01753   0.00934  -0.1139   0.3404   1.0000
   7.000   1.4022   0.01807   0.00985  -0.1132   0.3301   1.0000
   7.250   1.4248   0.01864   0.01035  -0.1125   0.3198   1.0000
   7.500   1.4475   0.01912   0.01087  -0.1118   0.3094   1.0000
   7.750   1.4693   0.01974   0.01144  -0.1109   0.3000   1.0000
   8.000   1.4910   0.02023   0.01197  -0.1101   0.2899   1.0000
   8.250   1.5120   0.02082   0.01257  -0.1091   0.2802   1.0000
   8.500   1.5321   0.02142   0.01313  -0.1081   0.2705   1.0000
   8.750   1.5520   0.02195   0.01376  -0.1070   0.2602   1.0000
   9.000   1.5705   0.02264   0.01440  -0.1057   0.2512   1.0000
   9.250   1.5888   0.02323   0.01506  -0.1044   0.2418   1.0000
   9.500   1.6060   0.02396   0.01580  -0.1029   0.2334   1.0000
   9.750   1.6221   0.02467   0.01653  -0.1013   0.2251   1.0000
  10.000   1.6371   0.02543   0.01734  -0.0996   0.2170   1.0000
  10.250   1.6497   0.02621   0.01810  -0.0976   0.2093   1.0000
  10.500   1.6605   0.02702   0.01898  -0.0952   0.2019   1.0000
  10.750   1.6696   0.02790   0.01988  -0.0927   0.1953   1.0000
  11.000   1.6797   0.02892   0.02095  -0.0906   0.1893   1.0000
  11.250   1.6894   0.02992   0.02204  -0.0885   0.1835   1.0000
  11.500   1.6986   0.03117   0.02320  -0.0866   0.1782   1.0000
  11.750   1.7081   0.03228   0.02449  -0.0848   0.1733   1.0000
  12.000   1.7170   0.03352   0.02583  -0.0831   0.1686   1.0000
  12.250   1.7258   0.03492   0.02716  -0.0815   0.1641   1.0000
  12.500   1.7334   0.03633   0.02875  -0.0800   0.1598   1.0000
  12.750   1.7403   0.03783   0.03038  -0.0787   0.1554   1.0000
  13.000   1.7469   0.03944   0.03199  -0.0774   0.1514   1.0000
  13.250   1.7541   0.04109   0.03374  -0.0761   0.1478   1.0000
  13.500   1.7597   0.04287   0.03570  -0.0750   0.1441   1.0000
  13.750   1.7640   0.04478   0.03772  -0.0741   0.1403   1.0000
  14.000   1.7678   0.04676   0.03966  -0.0730   0.1363   1.0000
  14.250   1.7702   0.04899   0.04212  -0.0722   0.1328   1.0000
  14.500   1.7721   0.05131   0.04462  -0.0716   0.1290   1.0000
  14.750   1.7718   0.05388   0.04726  -0.0711   0.1251   1.0000
  15.000   1.7711   0.05656   0.05003  -0.0706   0.1213   1.0000
  15.250   1.7694   0.05955   0.05325  -0.0705   0.1166   1.0000
  15.500   1.7652   0.06289   0.05667  -0.0706   0.1121   1.0000
  15.750   1.7616   0.06631   0.06024  -0.0707   0.1074   1.0000
  16.000   1.7568   0.07010   0.06420  -0.0712   0.1015   1.0000
  16.250   1.7491   0.07437   0.06858  -0.0719   0.0955   1.0000
  16.500   1.7386   0.07921   0.07354  -0.0729   0.0881   1.0000
  16.750   1.7269   0.08437   0.07881  -0.0740   0.0787   1.0000
  17.000   1.7104   0.09036   0.08487  -0.0755   0.0691   1.0000
  17.250   1.6905   0.09704   0.09161  -0.0774   0.0602   1.0000
  17.500   1.6688   0.10418   0.09880  -0.0797   0.0535   1.0000
  17.750   1.6463   0.11165   0.10634  -0.0824   0.0492   1.0000
  18.000   1.6249   0.11913   0.11392  -0.0853   0.0458   1.0000
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