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

GOE 621 AIRFOIL (goe621-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 621 AIRFOIL (goe621-il)
Reynolds number: 1,000,000
Max Cl/Cd: 120.74 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe621-il-1000000.txt
Download as CSV file: xf-goe621-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 621 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
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.7425   0.05397   0.05128  -0.1023   0.9959   0.0276
 -14.500  -0.7622   0.04554   0.04265  -0.1118   0.9892   0.0277
 -14.250  -0.7641   0.03905   0.03598  -0.1210   0.9849   0.0278
 -14.000  -0.7525   0.03346   0.03020  -0.1313   0.9819   0.0281
 -13.750  -0.7387   0.02964   0.02619  -0.1387   0.9769   0.0282
 -13.500  -0.7191   0.02734   0.02373  -0.1428   0.9724   0.0285
 -13.250  -0.6987   0.02568   0.02193  -0.1450   0.9671   0.0287
 -13.000  -0.6901   0.02461   0.02073  -0.1436   0.9580   0.0289
 -12.750  -0.6808   0.02369   0.01969  -0.1420   0.9505   0.0291
 -12.500  -0.6691   0.02302   0.01892  -0.1401   0.9433   0.0293
 -12.250  -0.6544   0.02244   0.01822  -0.1386   0.9372   0.0295
 -12.000  -0.6410   0.02180   0.01749  -0.1367   0.9304   0.0296
 -11.750  -0.6323   0.02035   0.01588  -0.1346   0.9238   0.0298
 -11.500  -0.6203   0.01924   0.01470  -0.1326   0.9175   0.0302
 -11.250  -0.6038   0.01845   0.01385  -0.1311   0.9114   0.0305
 -11.000  -0.5842   0.01785   0.01319  -0.1299   0.9060   0.0307
 -10.750  -0.5643   0.01733   0.01263  -0.1287   0.8998   0.0310
 -10.500  -0.5433   0.01683   0.01207  -0.1277   0.8934   0.0313
 -10.250  -0.5218   0.01634   0.01151  -0.1267   0.8870   0.0316
 -10.000  -0.5001   0.01585   0.01096  -0.1257   0.8795   0.0319
  -9.750  -0.4778   0.01538   0.01040  -0.1248   0.8724   0.0323
  -9.500  -0.4552   0.01492   0.00989  -0.1239   0.8644   0.0326
  -9.250  -0.4319   0.01453   0.00941  -0.1230   0.8561   0.0330
  -9.000  -0.4080   0.01418   0.00900  -0.1223   0.8469   0.0334
  -8.750  -0.3843   0.01383   0.00855  -0.1214   0.8371   0.0336
  -8.500  -0.3600   0.01352   0.00817  -0.1207   0.8260   0.0339
  -8.250  -0.3383   0.01293   0.00748  -0.1196   0.8147   0.0343
  -8.000  -0.3165   0.01241   0.00688  -0.1185   0.8029   0.0349
  -7.750  -0.2925   0.01206   0.00648  -0.1178   0.7915   0.0354
  -7.500  -0.2679   0.01180   0.00615  -0.1171   0.7810   0.0359
  -7.250  -0.2431   0.01156   0.00584  -0.1164   0.7704   0.0364
  -7.000  -0.2178   0.01132   0.00555  -0.1158   0.7611   0.0370
  -6.750  -0.1926   0.01112   0.00527  -0.1151   0.7520   0.0376
  -6.500  -0.1666   0.01092   0.00501  -0.1146   0.7445   0.0381
  -6.250  -0.1405   0.01076   0.00479  -0.1142   0.7372   0.0386
  -6.000  -0.1157   0.01044   0.00441  -0.1135   0.7308   0.0396
  -5.750  -0.0897   0.01019   0.00414  -0.1130   0.7245   0.0407
  -5.500  -0.0637   0.01003   0.00393  -0.1125   0.7179   0.0416
  -5.250  -0.0370   0.00988   0.00374  -0.1121   0.7120   0.0427
  -5.000  -0.0101   0.00974   0.00357  -0.1118   0.7058   0.0437
  -4.750   0.0157   0.00956   0.00332  -0.1112   0.6991   0.0453
  -4.500   0.0424   0.00937   0.00314  -0.1108   0.6938   0.0472
  -4.250   0.0696   0.00924   0.00299  -0.1105   0.6886   0.0493
  -4.000   0.0960   0.00909   0.00280  -0.1101   0.6831   0.0523
  -3.750   0.1228   0.00896   0.00266  -0.1097   0.6778   0.0562
  -3.500   0.1498   0.00877   0.00250  -0.1094   0.6733   0.0636
  -3.250   0.1762   0.00857   0.00238  -0.1090   0.6682   0.0808
  -3.000   0.2025   0.00846   0.00231  -0.1085   0.6627   0.0996
  -2.750   0.2299   0.00835   0.00224  -0.1083   0.6581   0.1107
  -2.500   0.2574   0.00827   0.00217  -0.1080   0.6531   0.1193
  -2.250   0.2842   0.00820   0.00211  -0.1077   0.6478   0.1292
  -2.000   0.3110   0.00813   0.00205  -0.1073   0.6424   0.1414
  -1.750   0.3382   0.00801   0.00200  -0.1071   0.6375   0.1586
  -1.500   0.3648   0.00788   0.00195  -0.1067   0.6326   0.1852
  -1.250   0.3911   0.00780   0.00193  -0.1063   0.6278   0.2143
  -1.000   0.4180   0.00770   0.00192  -0.1060   0.6237   0.2436
  -0.750   0.4451   0.00761   0.00191  -0.1057   0.6191   0.2707
  -0.500   0.4718   0.00756   0.00192  -0.1053   0.6138   0.2949
  -0.250   0.4980   0.00756   0.00193  -0.1049   0.6082   0.3178
   0.000   0.5254   0.00750   0.00195  -0.1046   0.6035   0.3385
   0.250   0.5523   0.00748   0.00196  -0.1043   0.5980   0.3570
   0.500   0.5783   0.00750   0.00198  -0.1038   0.5920   0.3734
   0.750   0.6054   0.00748   0.00201  -0.1035   0.5864   0.3885
   1.000   0.6317   0.00748   0.00203  -0.1031   0.5790   0.4034
   1.250   0.6575   0.00751   0.00206  -0.1025   0.5722   0.4190
   1.500   0.6840   0.00751   0.00209  -0.1021   0.5644   0.4360
   1.750   0.7087   0.00755   0.00214  -0.1014   0.5555   0.4557
   2.000   0.7341   0.00754   0.00218  -0.1008   0.5453   0.4812
   2.250   0.7581   0.00756   0.00224  -0.0999   0.5341   0.5121
   2.500   0.7805   0.00756   0.00232  -0.0988   0.5201   0.5556
   2.750   0.7962   0.00731   0.00244  -0.0963   0.5033   0.7093
   3.000   0.8850   0.00733   0.00285  -0.1095   0.4600   0.9901
   3.250   0.9263   0.00793   0.00315  -0.1128   0.4085   1.0000
   3.500   0.9404   0.00833   0.00337  -0.1101   0.3777   1.0000
   3.750   0.9563   0.00866   0.00357  -0.1078   0.3566   1.0000
   4.000   0.9742   0.00891   0.00374  -0.1058   0.3432   1.0000
   4.250   0.9920   0.00916   0.00391  -0.1038   0.3323   1.0000
   4.500   1.0107   0.00937   0.00407  -0.1019   0.3237   1.0000
   4.750   1.0286   0.00960   0.00425  -0.0999   0.3157   1.0000
   5.000   1.0478   0.00977   0.00440  -0.0982   0.3098   1.0000
   5.250   1.0630   0.00999   0.00458  -0.0957   0.3038   1.0000
   5.500   1.0790   0.01017   0.00474  -0.0933   0.2988   1.0000
   5.750   1.0968   0.01034   0.00490  -0.0913   0.2943   1.0000
   6.000   1.1137   0.01055   0.00509  -0.0892   0.2894   1.0000
   6.250   1.1297   0.01082   0.00533  -0.0870   0.2839   1.0000
   6.500   1.1497   0.01099   0.00551  -0.0855   0.2805   1.0000
   6.750   1.1689   0.01120   0.00571  -0.0839   0.2761   1.0000
   7.000   1.1869   0.01147   0.00596  -0.0822   0.2713   1.0000
   7.250   1.2042   0.01178   0.00625  -0.0804   0.2662   1.0000
   7.500   1.2250   0.01198   0.00646  -0.0792   0.2624   1.0000
   7.750   1.2438   0.01226   0.00673  -0.0778   0.2574   1.0000
   8.000   1.2610   0.01262   0.00706  -0.0761   0.2518   1.0000
   8.250   1.2805   0.01290   0.00735  -0.0748   0.2479   1.0000
   8.500   1.2999   0.01320   0.00765  -0.0736   0.2433   1.0000
   8.750   1.3176   0.01358   0.00802  -0.0721   0.2379   1.0000
   9.000   1.3351   0.01398   0.00841  -0.0706   0.2329   1.0000
   9.250   1.3544   0.01431   0.00876  -0.0695   0.2282   1.0000
   9.500   1.3708   0.01479   0.00920  -0.0679   0.2216   1.0000
   9.750   1.3881   0.01524   0.00966  -0.0666   0.2162   1.0000
  10.000   1.4051   0.01572   0.01012  -0.0652   0.2093   1.0000
  10.250   1.4197   0.01633   0.01069  -0.0636   0.2015   1.0000
  10.500   1.4359   0.01688   0.01124  -0.0623   0.1946   1.0000
  10.750   1.4496   0.01759   0.01191  -0.0607   0.1873   1.0000
  11.000   1.4649   0.01821   0.01253  -0.0593   0.1807   1.0000
  11.250   1.4769   0.01905   0.01333  -0.0576   0.1723   1.0000
  11.500   1.4911   0.01978   0.01405  -0.0563   0.1662   1.0000
  11.750   1.5023   0.02071   0.01496  -0.0547   0.1596   1.0000
  12.000   1.5168   0.02147   0.01573  -0.0534   0.1549   1.0000
  12.250   1.5280   0.02245   0.01670  -0.0520   0.1496   1.0000
  12.500   1.5403   0.02339   0.01764  -0.0507   0.1449   1.0000
  12.750   1.5535   0.02428   0.01856  -0.0495   0.1416   1.0000
  13.000   1.5630   0.02545   0.01972  -0.0481   0.1365   1.0000
  13.250   1.5742   0.02653   0.02081  -0.0469   0.1327   1.0000
  13.500   1.5869   0.02754   0.02186  -0.0459   0.1299   1.0000
  13.750   1.5984   0.02866   0.02300  -0.0449   0.1270   1.0000
  14.000   1.6075   0.02997   0.02432  -0.0437   0.1237   1.0000
  14.250   1.6163   0.03134   0.02571  -0.0426   0.1207   1.0000
  14.500   1.6291   0.03240   0.02682  -0.0418   0.1187   1.0000
  14.750   1.6396   0.03369   0.02815  -0.0410   0.1163   1.0000
  15.000   1.6476   0.03518   0.02965  -0.0400   0.1130   1.0000
  15.250   1.6533   0.03689   0.03138  -0.0390   0.1097   1.0000
  15.500   1.6641   0.03819   0.03273  -0.0383   0.1077   1.0000
  15.750   1.6736   0.03963   0.03422  -0.0376   0.1053   1.0000
  16.000   1.6793   0.04142   0.03602  -0.0368   0.1017   1.0000
  16.250   1.6829   0.04341   0.03802  -0.0359   0.0979   1.0000
  16.500   1.6916   0.04498   0.03965  -0.0353   0.0949   1.0000
  16.750   1.6937   0.04717   0.04183  -0.0346   0.0896   1.0000
  17.000   1.6970   0.04932   0.04400  -0.0340   0.0848   1.0000
  17.250   1.6892   0.05258   0.04720  -0.0331   0.0729   1.0000
  17.500   1.6724   0.05686   0.05141  -0.0323   0.0594   1.0000
  17.750   1.6503   0.06192   0.05642  -0.0317   0.0467   1.0000
  18.000   1.6183   0.06833   0.06280  -0.0314   0.0333   1.0000
  18.250   1.6001   0.07337   0.06788  -0.0315   0.0272   1.0000
  18.500   1.5800   0.07882   0.07337  -0.0319   0.0222   1.0000
  18.750   1.5659   0.08363   0.07826  -0.0324   0.0201   1.0000
<< Back to GOE 621 AIRFOIL (goe621-il)

Polar data table (+)

Polar graphs


<< Back to GOE 621 AIRFOIL (goe621-il)