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GOE 15 AIRFOIL (goe15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 15 AIRFOIL (goe15-il)
Reynolds number: 1,000,000
Max Cl/Cd: 115.33 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe15-il-1000000-n5.txt
Download as CSV file: xf-goe15-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 15 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.0154   0.09945   0.09652  -0.0887   0.7399   0.0120
 -10.500  -0.0086   0.09691   0.09393  -0.0895   0.7298   0.0122
 -10.000   0.0032   0.09149   0.08845  -0.0912   0.7147   0.0132
  -9.750   0.0130   0.08971   0.08665  -0.0918   0.7080   0.0133
  -9.500   0.0225   0.08795   0.08486  -0.0924   0.7014   0.0136
  -9.250   0.0317   0.08603   0.08294  -0.0930   0.6962   0.0139
  -9.000   0.0397   0.08396   0.08086  -0.0936   0.6907   0.0142
  -8.500   0.0432   0.07784   0.07472  -0.0952   0.6809   0.0155
  -8.250   0.0506   0.07606   0.07294  -0.0954   0.6750   0.0156
  -8.000   0.0585   0.07459   0.07146  -0.0954   0.6690   0.0157
  -7.750   0.0651   0.07312   0.07000  -0.0953   0.6650   0.0159
  -7.500   0.0696   0.07166   0.06854  -0.0950   0.6585   0.0161
  -7.250   0.0768   0.06974   0.06662  -0.0957   0.6531   0.0162
  -7.000   0.0863   0.06774   0.06460  -0.0967   0.6483   0.0164
  -6.750   0.0977   0.06573   0.06258  -0.0979   0.6429   0.0169
  -6.500   0.1091   0.06343   0.06026  -0.0993   0.6367   0.0171
  -6.250   0.1215   0.06106   0.05786  -0.1008   0.6308   0.0174
  -6.000   0.1339   0.05752   0.05427  -0.1035   0.6244   0.0184
  -5.750   0.1508   0.05619   0.05290  -0.1042   0.6149   0.0186
  -5.500   0.1683   0.05444   0.05110  -0.1053   0.6037   0.0188
  -5.250   0.1860   0.05261   0.04920  -0.1064   0.5899   0.0190
  -5.000   0.2043   0.05075   0.04725  -0.1075   0.5733   0.0194
  -4.750   0.2230   0.04874   0.04513  -0.1087   0.5539   0.0196
  -4.500   0.2423   0.04671   0.04297  -0.1097   0.5319   0.0197
  -4.250   0.2624   0.04470   0.04081  -0.1108   0.5089   0.0200
  -4.000   0.2858   0.04099   0.03691  -0.1130   0.4902   0.0212
  -3.750   0.3066   0.03975   0.03556  -0.1133   0.4715   0.0213
  -3.500   0.3284   0.03852   0.03422  -0.1136   0.4569   0.0215
  -3.000   0.3747   0.03564   0.03115  -0.1145   0.4369   0.0219
  -2.750   0.3986   0.03421   0.02963  -0.1148   0.4299   0.0222
  -2.500   0.4231   0.03263   0.02795  -0.1151   0.4246   0.0224
  -2.250   0.4480   0.03110   0.02633  -0.1154   0.4198   0.0227
  -2.000   0.4730   0.02953   0.02466  -0.1155   0.4149   0.0231
  -1.500   0.5247   0.02527   0.02007  -0.1153   0.4066   0.0243
  -1.250   0.5495   0.02437   0.01911  -0.1151   0.4032   0.0245
  -1.000   0.5743   0.02359   0.01826  -0.1148   0.3998   0.0247
  -0.750   0.5992   0.02271   0.01730  -0.1144   0.3962   0.0249
  -0.500   0.6241   0.02190   0.01640  -0.1140   0.3924   0.0252
  -0.250   0.6496   0.02101   0.01542  -0.1136   0.3897   0.0259
   0.000   0.6755   0.01975   0.01403  -0.1130   0.3870   0.0265
   0.250   0.7015   0.01772   0.01176  -0.1119   0.3844   0.0275
   0.500   0.7268   0.01727   0.01125  -0.1115   0.3816   0.0277
   0.750   0.7520   0.01681   0.01073  -0.1110   0.3786   0.0280
   1.000   0.7770   0.01638   0.01023  -0.1104   0.3753   0.0283
   1.250   0.8025   0.01590   0.00968  -0.1098   0.3726   0.0291
   1.500   0.8283   0.01463   0.00822  -0.1088   0.3705   0.0304
   1.750   0.8537   0.01385   0.00731  -0.1081   0.3681   0.0311
   2.000   0.8792   0.01363   0.00705  -0.1076   0.3646   0.0314
   2.250   0.9042   0.01341   0.00677  -0.1070   0.3603   0.0318
   2.500   0.9289   0.01313   0.00641  -0.1063   0.3560   0.0326
   2.750   0.9542   0.01197   0.00507  -0.1054   0.3536   0.0346
   3.000   0.9797   0.01187   0.00496  -0.1050   0.3507   0.0349
   3.250   1.0049   0.01178   0.00485  -0.1044   0.3471   0.0354
   3.500   1.0294   0.01163   0.00466  -0.1038   0.3427   0.0361
   3.750   1.0526   0.01114   0.00405  -0.1028   0.3384   0.0382
   4.000   1.0774   0.01107   0.00399  -0.1022   0.3348   0.0386
   4.250   1.1020   0.01110   0.00404  -0.1016   0.3313   0.0390
   4.500   1.1261   0.01112   0.00405  -0.1009   0.3280   0.0396
   4.750   1.1496   0.01114   0.00406  -0.1001   0.3245   0.0403
   5.000   1.1733   0.01115   0.00406  -0.0993   0.3216   0.0415
   5.250   1.1971   0.01115   0.00407  -0.0986   0.3188   0.0422
   5.500   1.2204   0.01117   0.00409  -0.0978   0.3149   0.0429
   5.750   1.2433   0.01126   0.00418  -0.0969   0.3102   0.0434
   6.000   1.2657   0.01137   0.00429  -0.0959   0.3056   0.0442
   6.250   1.2889   0.01145   0.00438  -0.0951   0.3018   0.0449
   6.500   1.3114   0.01155   0.00450  -0.0942   0.2974   0.0462
   6.750   1.3328   0.01170   0.00463  -0.0930   0.2925   0.0469
   7.000   1.3541   0.01181   0.00475  -0.0919   0.2885   0.0476
   7.250   1.3745   0.01192   0.00488  -0.0906   0.2837   0.0486
   7.500   1.3932   0.01208   0.00504  -0.0889   0.2782   0.0494
   7.750   1.4118   0.01226   0.00522  -0.0873   0.2732   0.0507
   8.000   1.4307   0.01244   0.00542  -0.0857   0.2672   0.0520
   8.250   1.4463   0.01278   0.00570  -0.0836   0.2552   0.0530
   8.500   1.4609   0.01315   0.00602  -0.0814   0.2426   0.0545
   8.750   1.4760   0.01352   0.00635  -0.0793   0.2315   0.0558
   9.000   1.4897   0.01395   0.00674  -0.0770   0.2184   0.0575
   9.250   1.5031   0.01441   0.00715  -0.0748   0.2068   0.0589
   9.500   1.5158   0.01489   0.00760  -0.0724   0.1965   0.0621
   9.750   1.5277   0.01542   0.00809  -0.0701   0.1861   0.0664
  10.000   1.5396   0.01594   0.00863  -0.0677   0.1764   0.1457
  10.500   1.6128   0.01656   0.01035  -0.0746   0.1532   1.0000
  10.750   1.6256   0.01721   0.01097  -0.0728   0.1460   1.0000
  11.000   1.6381   0.01789   0.01165  -0.0710   0.1401   1.0000
  11.250   1.6512   0.01857   0.01232  -0.0693   0.1338   1.0000
  11.500   1.6604   0.01950   0.01322  -0.0673   0.1248   1.0000
  11.750   1.6667   0.02066   0.01431  -0.0651   0.1129   1.0000
  12.000   1.6665   0.02230   0.01585  -0.0624   0.0947   1.0000
  12.250   1.6635   0.02425   0.01771  -0.0598   0.0792   1.0000
  12.500   1.6552   0.02674   0.02012  -0.0571   0.0611   1.0000
  12.750   1.6446   0.02965   0.02296  -0.0547   0.0444   1.0000
  13.000   1.6233   0.03375   0.02698  -0.0522   0.0213   1.0000
  13.250   1.6190   0.03648   0.02975  -0.0509   0.0159   1.0000
  13.500   1.6214   0.03862   0.03195  -0.0500   0.0145   1.0000
  13.750   1.6234   0.04087   0.03426  -0.0492   0.0135   1.0000
  14.000   1.6241   0.04331   0.03677  -0.0485   0.0127   1.0000
  14.250   1.6236   0.04592   0.03944  -0.0478   0.0120   1.0000
  14.500   1.6246   0.04844   0.04204  -0.0473   0.0116   1.0000
  14.750   1.6247   0.05113   0.04480  -0.0469   0.0113   1.0000
  15.000   1.6236   0.05402   0.04778  -0.0467   0.0109   1.0000
  15.250   1.6208   0.05718   0.05102  -0.0465   0.0105   1.0000
  15.500   1.6166   0.06061   0.05452  -0.0464   0.0102   1.0000
  15.750   1.6115   0.06423   0.05822  -0.0465   0.0098   1.0000
  16.000   1.6057   0.06800   0.06208  -0.0467   0.0096   1.0000
  16.250   1.5977   0.07211   0.06628  -0.0471   0.0093   1.0000
  16.500   1.5920   0.07597   0.07022  -0.0474   0.0091   1.0000
  16.750   1.5858   0.07994   0.07428  -0.0479   0.0090   1.0000
  17.000   1.5792   0.08395   0.07838  -0.0484   0.0089   1.0000
  17.250   1.5720   0.08807   0.08258  -0.0490   0.0087   1.0000
  17.500   1.5645   0.09224   0.08684  -0.0496   0.0086   1.0000
  17.750   1.5572   0.09639   0.09108  -0.0503   0.0084   1.0000
  18.000   1.5483   0.10081   0.09558  -0.0511   0.0082   1.0000
  18.250   1.5407   0.10502   0.09987  -0.0519   0.0080   1.0000
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