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

GOE 650 AIRFOIL (goe650-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 650 AIRFOIL (goe650-il)
Reynolds number: 1,000,000
Max Cl/Cd: 109.58 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe650-il-1000000.txt
Download as CSV file: xf-goe650-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 650 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.500  -0.7347   0.12697   0.12461  -0.0498   1.0000   0.0230
 -18.250  -0.7560   0.11930   0.11684  -0.0539   1.0000   0.0233
 -18.000  -0.7740   0.11244   0.10989  -0.0575   1.0000   0.0235
 -17.750  -0.7891   0.10627   0.10364  -0.0608   1.0000   0.0239
 -17.500  -0.8017   0.10077   0.09806  -0.0636   1.0000   0.0240
 -17.250  -0.8146   0.09522   0.09244  -0.0665   1.0000   0.0242
 -17.000  -0.8241   0.09047   0.08762  -0.0689   1.0000   0.0243
 -16.750  -0.8356   0.08540   0.08248  -0.0714   1.0000   0.0245
 -16.500  -0.8470   0.08048   0.07749  -0.0739   1.0000   0.0246
 -16.250  -0.8563   0.07608   0.07301  -0.0760   1.0000   0.0247
 -16.000  -0.8668   0.07157   0.06844  -0.0782   1.0000   0.0248
 -15.750  -0.8803   0.06726   0.06407  -0.0799   1.0000   0.0250
 -15.500  -0.8933   0.06328   0.06005  -0.0813   1.0000   0.0253
 -15.250  -0.9093   0.05909   0.05582  -0.0828   1.0000   0.0254
 -15.000  -0.9283   0.05483   0.05151  -0.0840   1.0000   0.0255
 -14.750  -0.9512   0.05050   0.04712  -0.0849   1.0000   0.0256
 -14.500  -0.9811   0.04611   0.04268  -0.0850   1.0000   0.0256
 -14.250  -1.0023   0.04095   0.03744  -0.0885   0.9987   0.0257
 -14.000  -1.0002   0.03449   0.03085  -0.0990   0.9939   0.0259
 -13.750  -0.9825   0.02872   0.02492  -0.1094   0.9893   0.0262
 -13.500  -0.9559   0.02570   0.02176  -0.1156   0.9863   0.0266
 -13.250  -0.9271   0.02424   0.02022  -0.1186   0.9845   0.0272
 -13.000  -0.8978   0.02289   0.01877  -0.1214   0.9831   0.0276
 -12.750  -0.8671   0.02177   0.01756  -0.1239   0.9821   0.0281
 -12.500  -0.8475   0.02090   0.01661  -0.1235   0.9769   0.0284
 -12.250  -0.8183   0.02017   0.01581  -0.1248   0.9747   0.0287
 -12.000  -0.7916   0.01872   0.01426  -0.1266   0.9726   0.0294
 -11.750  -0.7618   0.01762   0.01311  -0.1284   0.9712   0.0300
 -11.500  -0.7298   0.01681   0.01224  -0.1301   0.9702   0.0306
 -11.250  -0.7037   0.01615   0.01153  -0.1304   0.9668   0.0311
 -11.000  -0.6771   0.01555   0.01088  -0.1307   0.9630   0.0317
 -10.750  -0.6452   0.01498   0.01025  -0.1319   0.9609   0.0323
 -10.500  -0.6127   0.01445   0.00967  -0.1332   0.9590   0.0329
 -10.250  -0.5797   0.01396   0.00911  -0.1346   0.9571   0.0333
 -10.000  -0.5525   0.01318   0.00827  -0.1350   0.9531   0.0343
  -9.750  -0.5272   0.01264   0.00769  -0.1348   0.9474   0.0351
  -9.500  -0.4962   0.01217   0.00716  -0.1357   0.9437   0.0360
  -9.250  -0.4638   0.01176   0.00670  -0.1367   0.9402   0.0370
  -9.000  -0.4398   0.01145   0.00634  -0.1359   0.9329   0.0377
  -8.750  -0.4100   0.01105   0.00588  -0.1364   0.9276   0.0389
  -8.500  -0.3832   0.01064   0.00543  -0.1362   0.9213   0.0405
  -8.250  -0.3567   0.01031   0.00507  -0.1360   0.9140   0.0423
  -8.000  -0.3281   0.01000   0.00470  -0.1361   0.9075   0.0448
  -7.750  -0.3037   0.00966   0.00435  -0.1353   0.8991   0.0494
  -7.500  -0.2771   0.00922   0.00395  -0.1352   0.8918   0.0648
  -7.250  -0.2527   0.00892   0.00372  -0.1344   0.8838   0.0794
  -7.000  -0.2253   0.00874   0.00354  -0.1342   0.8765   0.0883
  -6.750  -0.1986   0.00861   0.00339  -0.1338   0.8689   0.0935
  -6.500  -0.1717   0.00847   0.00324  -0.1334   0.8611   0.0991
  -6.250  -0.1445   0.00840   0.00312  -0.1331   0.8538   0.1027
  -6.000  -0.1178   0.00826   0.00297  -0.1326   0.8460   0.1072
  -5.750  -0.0906   0.00817   0.00285  -0.1323   0.8391   0.1116
  -5.500  -0.0636   0.00810   0.00275  -0.1319   0.8315   0.1149
  -5.250  -0.0367   0.00800   0.00261  -0.1315   0.8240   0.1197
  -5.000  -0.0098   0.00790   0.00252  -0.1311   0.8170   0.1244
  -4.750   0.0175   0.00785   0.00242  -0.1307   0.8102   0.1278
  -4.500   0.0447   0.00777   0.00231  -0.1304   0.8044   0.1326
  -4.250   0.0718   0.00767   0.00223  -0.1301   0.7985   0.1377
  -4.000   0.0993   0.00762   0.00215  -0.1297   0.7928   0.1417
  -3.750   0.1266   0.00756   0.00206  -0.1294   0.7874   0.1469
  -3.500   0.1537   0.00746   0.00199  -0.1291   0.7816   0.1529
  -3.250   0.1808   0.00743   0.00192  -0.1286   0.7746   0.1576
  -3.000   0.2076   0.00735   0.00184  -0.1282   0.7680   0.1652
  -2.750   0.2346   0.00729   0.00179  -0.1278   0.7613   0.1724
  -2.500   0.2614   0.00725   0.00172  -0.1274   0.7543   0.1797
  -2.250   0.2884   0.00717   0.00167  -0.1270   0.7478   0.1881
  -2.000   0.3151   0.00711   0.00162  -0.1265   0.7407   0.1982
  -1.750   0.3418   0.00707   0.00158  -0.1260   0.7338   0.2100
  -1.250   0.3949   0.00697   0.00153  -0.1250   0.7193   0.2420
  -0.750   0.4486   0.00687   0.00151  -0.1242   0.7059   0.2757
  -0.500   0.4751   0.00685   0.00152  -0.1237   0.6990   0.2927
  -0.250   0.5018   0.00681   0.00152  -0.1232   0.6907   0.3084
   0.000   0.5279   0.00682   0.00154  -0.1226   0.6827   0.3220
   0.250   0.5545   0.00680   0.00155  -0.1221   0.6734   0.3355
   0.750   0.6056   0.00685   0.00159  -0.1207   0.6502   0.3601
   1.000   0.6309   0.00689   0.00162  -0.1199   0.6349   0.3712
   1.250   0.6548   0.00697   0.00165  -0.1189   0.6154   0.3823
   1.500   0.6781   0.00707   0.00171  -0.1177   0.5918   0.3940
   1.750   0.7000   0.00725   0.00178  -0.1163   0.5655   0.4039
   2.000   0.7225   0.00741   0.00188  -0.1150   0.5439   0.4159
   2.250   0.7454   0.00756   0.00199  -0.1139   0.5249   0.4273
   2.500   0.7685   0.00772   0.00209  -0.1127   0.5070   0.4385
   2.750   0.7916   0.00787   0.00221  -0.1116   0.4898   0.4508
   3.000   0.8145   0.00802   0.00232  -0.1104   0.4716   0.4638
   3.250   0.8370   0.00819   0.00245  -0.1092   0.4503   0.4783
   3.500   0.8583   0.00839   0.00258  -0.1077   0.4262   0.4934
   3.750   0.8786   0.00862   0.00274  -0.1061   0.3969   0.5127
   4.000   0.8975   0.00888   0.00293  -0.1043   0.3670   0.5370
   4.250   0.9161   0.00915   0.00314  -0.1024   0.3418   0.5659
   4.500   0.9358   0.00934   0.00335  -0.1006   0.3243   0.5974
   4.750   0.9548   0.00947   0.00353  -0.0988   0.3104   0.6402
   5.000   0.9715   0.00948   0.00371  -0.0964   0.2992   0.7187
   5.250   1.0421   0.00951   0.00416  -0.1060   0.2798   1.0000
   5.500   1.0626   0.00977   0.00435  -0.1045   0.2673   1.0000
   5.750   1.0814   0.01004   0.00455  -0.1026   0.2555   1.0000
   6.000   1.1015   0.01024   0.00472  -0.1009   0.2464   1.0000
   6.250   1.1204   0.01050   0.00492  -0.0991   0.2362   1.0000
   6.500   1.1402   0.01073   0.00512  -0.0974   0.2278   1.0000
   6.750   1.1597   0.01099   0.00534  -0.0957   0.2196   1.0000
   7.000   1.1791   0.01126   0.00557  -0.0941   0.2110   1.0000
   7.250   1.1987   0.01153   0.00580  -0.0925   0.2026   1.0000
   7.500   1.2174   0.01185   0.00607  -0.0907   0.1933   1.0000
   7.750   1.2372   0.01212   0.00633  -0.0892   0.1856   1.0000
   8.000   1.2554   0.01248   0.00663  -0.0875   0.1768   1.0000
   8.250   1.2753   0.01277   0.00691  -0.0860   0.1701   1.0000
   8.500   1.2928   0.01317   0.00726  -0.0842   0.1612   1.0000
   8.750   1.3121   0.01350   0.00758  -0.0828   0.1541   1.0000
   9.000   1.3295   0.01393   0.00796  -0.0810   0.1461   1.0000
   9.250   1.3482   0.01429   0.00832  -0.0795   0.1401   1.0000
   9.500   1.3652   0.01476   0.00875  -0.0778   0.1330   1.0000
   9.750   1.3834   0.01516   0.00914  -0.0763   0.1272   1.0000
  10.000   1.3999   0.01567   0.00962  -0.0746   0.1210   1.0000
  10.250   1.4180   0.01610   0.01006  -0.0732   0.1164   1.0000
  10.500   1.4341   0.01665   0.01058  -0.0715   0.1107   1.0000
  10.750   1.4510   0.01716   0.01109  -0.0700   0.1059   1.0000
  11.000   1.4671   0.01772   0.01164  -0.0684   0.1007   1.0000
  11.250   1.4821   0.01837   0.01227  -0.0667   0.0938   1.0000
  11.500   1.4958   0.01909   0.01296  -0.0650   0.0870   1.0000
  11.750   1.5094   0.01985   0.01369  -0.0633   0.0788   1.0000
  12.000   1.5157   0.02109   0.01479  -0.0608   0.0610   1.0000
  12.250   1.5134   0.02294   0.01647  -0.0576   0.0397   1.0000
  12.500   1.5205   0.02421   0.01773  -0.0554   0.0352   1.0000
  12.750   1.5312   0.02526   0.01881  -0.0538   0.0333   1.0000
  13.000   1.5415   0.02637   0.01995  -0.0521   0.0319   1.0000
  13.250   1.5501   0.02763   0.02125  -0.0505   0.0306   1.0000
  13.500   1.5570   0.02904   0.02270  -0.0487   0.0295   1.0000
  13.750   1.5674   0.03020   0.02393  -0.0474   0.0288   1.0000
  14.000   1.5771   0.03147   0.02525  -0.0461   0.0281   1.0000
  14.250   1.5850   0.03289   0.02672  -0.0447   0.0274   1.0000
  14.500   1.5917   0.03445   0.02834  -0.0434   0.0268   1.0000
  14.750   1.5960   0.03626   0.03022  -0.0421   0.0261   1.0000
  15.000   1.5975   0.03840   0.03242  -0.0407   0.0255   1.0000
  15.250   1.6016   0.04034   0.03443  -0.0396   0.0249   1.0000
  15.500   1.6077   0.04215   0.03631  -0.0387   0.0246   1.0000
  15.750   1.6127   0.04411   0.03835  -0.0379   0.0242   1.0000
  16.000   1.6161   0.04629   0.04060  -0.0371   0.0237   1.0000
  16.250   1.6185   0.04860   0.04298  -0.0365   0.0232   1.0000
  16.500   1.6189   0.05120   0.04566  -0.0359   0.0229   1.0000
  16.750   1.6170   0.05415   0.04868  -0.0355   0.0225   1.0000
  17.000   1.6120   0.05756   0.05218  -0.0353   0.0221   1.0000
  17.250   1.6035   0.06151   0.05623  -0.0353   0.0218   1.0000
  17.500   1.5917   0.06602   0.06085  -0.0356   0.0214   1.0000
  17.750   1.5898   0.06937   0.06429  -0.0360   0.0212   1.0000
  18.000   1.5860   0.07304   0.06805  -0.0364   0.0210   1.0000
  18.250   1.5818   0.07677   0.07188  -0.0370   0.0207   1.0000
  18.500   1.5763   0.08072   0.07593  -0.0377   0.0204   1.0000
  18.750   1.5656   0.08550   0.08081  -0.0388   0.0202   1.0000
  19.000   1.5538   0.09051   0.08593  -0.0400   0.0200   1.0000
  19.250   1.5409   0.09572   0.09124  -0.0415   0.0198   1.0000
<< Back to GOE 650 AIRFOIL (goe650-il)

Polar data table (+)

Polar graphs


<< Back to GOE 650 AIRFOIL (goe650-il)