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GOE 621 AIRFOIL (goe621-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 621 AIRFOIL (goe621-il)
Reynolds number: 200,000
Max Cl/Cd: 74.72 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe621-il-200000.txt
Download as CSV file: xf-goe621-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1503   0.09027   0.08665  -0.0828   0.9661   0.0939
  -9.000  -0.1252   0.08779   0.08416  -0.0843   0.9611   0.0957
  -8.750  -0.2427   0.05156   0.04755  -0.1252   0.9397   0.0733
  -8.500  -0.3176   0.03787   0.03264  -0.1256   0.9153   0.0648
  -8.250  -0.3031   0.03452   0.02875  -0.1260   0.9090   0.0643
  -8.000  -0.2918   0.03225   0.02617  -0.1244   0.8996   0.0644
  -7.750  -0.2719   0.02982   0.02347  -0.1242   0.8936   0.0647
  -7.500  -0.2442   0.02794   0.02143  -0.1249   0.8902   0.0655
  -7.250  -0.2294   0.02702   0.02042  -0.1228   0.8801   0.0665
  -7.000  -0.2019   0.02581   0.01908  -0.1229   0.8755   0.0677
  -6.750  -0.1770   0.02457   0.01763  -0.1225   0.8703   0.0689
  -6.500  -0.1579   0.02354   0.01640  -0.1210   0.8618   0.0699
  -6.250  -0.1302   0.02240   0.01502  -0.1208   0.8576   0.0712
  -6.000  -0.1057   0.02160   0.01401  -0.1201   0.8518   0.0723
  -5.750  -0.0832   0.02060   0.01301  -0.1192   0.8448   0.0740
  -5.500  -0.0542   0.01991   0.01231  -0.1192   0.8404   0.0765
  -5.250  -0.0280   0.01938   0.01169  -0.1187   0.8351   0.0795
  -5.000  -0.0049   0.01889   0.01109  -0.1176   0.8281   0.0820
  -4.750   0.0227   0.01816   0.01042  -0.1175   0.8237   0.0855
  -4.500   0.0521   0.01766   0.00985  -0.1175   0.8199   0.0903
  -4.250   0.0720   0.01730   0.00953  -0.1160   0.8122   0.0954
  -4.000   0.0998   0.01696   0.00912  -0.1157   0.8074   0.1037
  -3.750   0.1288   0.01638   0.00857  -0.1157   0.8039   0.1159
  -3.500   0.1490   0.01607   0.00834  -0.1143   0.7972   0.1319
  -3.250   0.1736   0.01564   0.00803  -0.1137   0.7917   0.1541
  -3.000   0.2036   0.01529   0.00767  -0.1138   0.7875   0.1787
  -2.750   0.2266   0.01511   0.00761  -0.1129   0.7809   0.2006
  -2.500   0.2524   0.01488   0.00744  -0.1122   0.7742   0.2270
  -2.250   0.2829   0.01458   0.00720  -0.1124   0.7694   0.2603
  -2.000   0.3050   0.01455   0.00728  -0.1112   0.7622   0.2921
  -1.750   0.3318   0.01445   0.00720  -0.1107   0.7559   0.3254
  -1.500   0.3629   0.01434   0.00706  -0.1109   0.7511   0.3596
  -1.250   0.3835   0.01436   0.00719  -0.1094   0.7429   0.3840
  -1.000   0.4118   0.01424   0.00705  -0.1091   0.7366   0.4080
  -0.750   0.4397   0.01419   0.00698  -0.1088   0.7312   0.4301
  -0.500   0.4626   0.01419   0.00705  -0.1077   0.7244   0.4501
  -0.250   0.4908   0.01409   0.00694  -0.1075   0.7189   0.4720
   0.000   0.5187   0.01400   0.00690  -0.1073   0.7139   0.4949
   0.250   0.5404   0.01397   0.00699  -0.1060   0.7070   0.5196
   0.500   0.5674   0.01380   0.00690  -0.1056   0.7012   0.5508
   0.750   0.5935   0.01359   0.00685  -0.1049   0.6957   0.5966
   1.000   0.6113   0.01312   0.00698  -0.1025   0.6883   0.7302
   1.250   0.7370   0.01267   0.00673  -0.1221   0.6812   1.0000
   1.500   0.7580   0.01280   0.00681  -0.1206   0.6735   1.0000
   1.750   0.7823   0.01285   0.00676  -0.1197   0.6658   1.0000
   2.000   0.8067   0.01294   0.00675  -0.1188   0.6586   1.0000
   2.250   0.8282   0.01302   0.00680  -0.1174   0.6501   1.0000
   2.500   0.8545   0.01306   0.00671  -0.1168   0.6427   1.0000
   2.750   0.8738   0.01314   0.00679  -0.1149   0.6325   1.0000
   3.000   0.8981   0.01318   0.00674  -0.1140   0.6236   1.0000
   3.250   0.9182   0.01323   0.00677  -0.1122   0.6128   1.0000
   3.500   0.9390   0.01330   0.00679  -0.1106   0.6017   1.0000
   3.750   0.9616   0.01333   0.00673  -0.1093   0.5901   1.0000
   4.000   0.9796   0.01340   0.00677  -0.1072   0.5757   1.0000
   4.250   0.9972   0.01350   0.00681  -0.1050   0.5596   1.0000
   4.500   1.0142   0.01361   0.00685  -0.1027   0.5416   1.0000
   4.750   1.0296   0.01378   0.00691  -0.1001   0.5212   1.0000
   5.000   1.0426   0.01402   0.00705  -0.0971   0.4977   1.0000
   5.250   1.0549   0.01434   0.00721  -0.0940   0.4743   1.0000
   5.500   1.0666   0.01475   0.00744  -0.0910   0.4529   1.0000
   5.750   1.0783   0.01519   0.00773  -0.0880   0.4336   1.0000
   6.000   1.0893   0.01565   0.00805  -0.0849   0.4174   1.0000
   6.250   1.1011   0.01614   0.00839  -0.0820   0.4038   1.0000
   6.500   1.1144   0.01659   0.00879  -0.0795   0.3916   1.0000
   6.750   1.1292   0.01708   0.00919  -0.0773   0.3812   1.0000
   7.000   1.1449   0.01759   0.00961  -0.0753   0.3719   1.0000
   7.250   1.1615   0.01807   0.01006  -0.0735   0.3634   1.0000
   7.500   1.1784   0.01858   0.01051  -0.0718   0.3553   1.0000
   7.750   1.1957   0.01910   0.01099  -0.0702   0.3476   1.0000
   8.000   1.2117   0.01960   0.01148  -0.0684   0.3401   1.0000
   8.250   1.2308   0.02017   0.01197  -0.0672   0.3330   1.0000
   8.500   1.2450   0.02067   0.01253  -0.0652   0.3259   1.0000
   8.750   1.2639   0.02125   0.01302  -0.0640   0.3192   1.0000
   9.000   1.2794   0.02180   0.01362  -0.0623   0.3129   1.0000
   9.250   1.2939   0.02236   0.01422  -0.0605   0.3064   1.0000
   9.500   1.3150   0.02300   0.01474  -0.0598   0.2999   1.0000
   9.750   1.3252   0.02360   0.01547  -0.0574   0.2938   1.0000
  10.000   1.3389   0.02422   0.01610  -0.0556   0.2875   1.0000
  10.250   1.3555   0.02491   0.01675  -0.0543   0.2812   1.0000
  10.500   1.3649   0.02561   0.01756  -0.0521   0.2748   1.0000
  10.750   1.3784   0.02632   0.01822  -0.0505   0.2686   1.0000
  11.000   1.3894   0.02712   0.01909  -0.0486   0.2622   1.0000
  11.250   1.3986   0.02794   0.01998  -0.0466   0.2559   1.0000
  11.500   1.4156   0.02870   0.02062  -0.0456   0.2500   1.0000
  11.750   1.4210   0.02971   0.02180  -0.0434   0.2440   1.0000
  12.000   1.4308   0.03063   0.02275  -0.0417   0.2383   1.0000
  12.250   1.4453   0.03152   0.02360  -0.0405   0.2328   1.0000
  12.500   1.4518   0.03266   0.02487  -0.0386   0.2272   1.0000
  12.750   1.4622   0.03367   0.02589  -0.0372   0.2222   1.0000
  13.000   1.4756   0.03466   0.02684  -0.0361   0.2171   1.0000
  13.250   1.4810   0.03596   0.02829  -0.0344   0.2121   1.0000
  13.500   1.4887   0.03716   0.02951  -0.0331   0.2072   1.0000
  13.750   1.5039   0.03811   0.03039  -0.0322   0.2027   1.0000
  14.000   1.5056   0.03972   0.03217  -0.0306   0.1982   1.0000
  14.250   1.5127   0.04108   0.03360  -0.0294   0.1940   1.0000
  14.500   1.5238   0.04222   0.03470  -0.0285   0.1901   1.0000
  14.750   1.5318   0.04367   0.03623  -0.0274   0.1863   1.0000
  15.000   1.5357   0.04539   0.03809  -0.0263   0.1827   1.0000
  15.250   1.5418   0.04696   0.03971  -0.0254   0.1791   1.0000
  15.500   1.5523   0.04821   0.04091  -0.0247   0.1755   1.0000
  15.750   1.5606   0.04977   0.04256  -0.0239   0.1725   1.0000
  16.000   1.5617   0.05189   0.04486  -0.0230   0.1696   1.0000
  16.250   1.5657   0.05379   0.04687  -0.0223   0.1666   1.0000
  16.500   1.5705   0.05560   0.04871  -0.0218   0.1634   1.0000
  16.750   1.5863   0.05650   0.04952  -0.0212   0.1600   1.0000
  17.000   1.5819   0.05932   0.05257  -0.0207   0.1578   1.0000
  17.250   1.5795   0.06202   0.05544  -0.0203   0.1550   1.0000
  17.500   1.5797   0.06450   0.05802  -0.0201   0.1521   1.0000
  17.750   1.5832   0.06662   0.06018  -0.0199   0.1493   1.0000
  18.000   1.5912   0.06827   0.06180  -0.0196   0.1459   1.0000
  18.250   1.5825   0.07197   0.06573  -0.0198   0.1437   1.0000
  18.500   1.5759   0.07552   0.06945  -0.0202   0.1409   1.0000
  18.750   1.5723   0.07874   0.07276  -0.0206   0.1377   1.0000
  19.000   1.5773   0.08078   0.07474  -0.0208   0.1342   1.0000
  19.250   1.5670   0.08506   0.07921  -0.0217   0.1316   1.0000
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