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

GOE 620 AIRFOIL (goe620-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 620 AIRFOIL (goe620-il)
Reynolds number: 1,000,000
Max Cl/Cd: 117.55 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe620-il-1000000.txt
Download as CSV file: xf-goe620-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 620 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
  ------ -------- --------- --------- -------- -------- --------
 -16.750  -0.6728   0.07496   0.07225  -0.1074   0.9947   0.0317
 -16.500  -0.6913   0.06687   0.06401  -0.1152   0.9930   0.0320
 -16.250  -0.7104   0.05985   0.05684  -0.1215   0.9902   0.0321
 -16.000  -0.7184   0.05414   0.05099  -0.1275   0.9873   0.0323
 -15.750  -0.7212   0.04894   0.04566  -0.1336   0.9844   0.0324
 -15.500  -0.7181   0.04421   0.04082  -0.1398   0.9820   0.0325
 -15.250  -0.7137   0.04008   0.03657  -0.1450   0.9783   0.0326
 -15.000  -0.7162   0.03548   0.03183  -0.1500   0.9718   0.0329
 -14.750  -0.7042   0.03176   0.02801  -0.1557   0.9678   0.0332
 -14.500  -0.6899   0.02892   0.02509  -0.1601   0.9596   0.0335
 -14.250  -0.6606   0.02662   0.02272  -0.1662   0.9544   0.0339
 -14.000  -0.6280   0.02457   0.02059  -0.1725   0.9486   0.0342
 -13.750  -0.5968   0.02300   0.01891  -0.1773   0.9400   0.0345
 -13.500  -0.5704   0.02183   0.01763  -0.1800   0.9291   0.0348
 -13.250  -0.5477   0.02102   0.01670  -0.1811   0.9165   0.0353
 -13.000  -0.5358   0.02025   0.01580  -0.1799   0.9012   0.0356
 -12.750  -0.5292   0.01967   0.01510  -0.1771   0.8854   0.0359
 -12.500  -0.5235   0.01919   0.01450  -0.1739   0.8707   0.0361
 -12.250  -0.5117   0.01871   0.01391  -0.1716   0.8582   0.0363
 -12.000  -0.4978   0.01829   0.01336  -0.1697   0.8468   0.0366
 -11.750  -0.4821   0.01792   0.01291  -0.1679   0.8367   0.0368
 -11.500  -0.4679   0.01738   0.01226  -0.1659   0.8272   0.0371
 -11.250  -0.4568   0.01656   0.01137  -0.1636   0.8179   0.0375
 -11.000  -0.4401   0.01610   0.01084  -0.1619   0.8099   0.0379
 -10.750  -0.4211   0.01570   0.01040  -0.1606   0.8031   0.0383
 -10.500  -0.4010   0.01538   0.01003  -0.1594   0.7963   0.0387
 -10.250  -0.3800   0.01509   0.00968  -0.1582   0.7901   0.0392
 -10.000  -0.3585   0.01477   0.00931  -0.1572   0.7841   0.0396
  -9.750  -0.3368   0.01450   0.00897  -0.1561   0.7778   0.0402
  -9.500  -0.3144   0.01425   0.00864  -0.1552   0.7723   0.0407
  -9.250  -0.2911   0.01397   0.00833  -0.1544   0.7678   0.0412
  -9.000  -0.2675   0.01375   0.00804  -0.1536   0.7630   0.0415
  -8.750  -0.2476   0.01325   0.00747  -0.1523   0.7585   0.0421
  -8.500  -0.2261   0.01284   0.00703  -0.1512   0.7540   0.0427
  -8.250  -0.2025   0.01255   0.00673  -0.1504   0.7506   0.0433
  -8.000  -0.1783   0.01230   0.00646  -0.1497   0.7467   0.0440
  -7.750  -0.1539   0.01208   0.00620  -0.1490   0.7428   0.0447
  -7.500  -0.1293   0.01189   0.00595  -0.1484   0.7388   0.0454
  -7.250  -0.1039   0.01171   0.00573  -0.1478   0.7350   0.0461
  -7.000  -0.0780   0.01156   0.00555  -0.1473   0.7320   0.0467
  -6.750  -0.0554   0.01115   0.00513  -0.1464   0.7286   0.0477
  -6.500  -0.0310   0.01090   0.00486  -0.1457   0.7250   0.0487
  -6.250  -0.0058   0.01072   0.00465  -0.1451   0.7212   0.0496
  -6.000   0.0203   0.01059   0.00446  -0.1446   0.7171   0.0506
  -5.750   0.0459   0.01042   0.00428  -0.1441   0.7144   0.0516
  -5.500   0.0721   0.01028   0.00413  -0.1436   0.7112   0.0523
  -5.250   0.0964   0.00999   0.00382  -0.1429   0.7077   0.0540
  -5.000   0.1218   0.00983   0.00364  -0.1423   0.7039   0.0556
  -4.750   0.1480   0.00973   0.00349  -0.1418   0.6998   0.0571
  -4.500   0.1743   0.00961   0.00336  -0.1414   0.6966   0.0584
  -4.250   0.1995   0.00939   0.00316  -0.1407   0.6933   0.0609
  -4.000   0.2252   0.00924   0.00301  -0.1402   0.6894   0.0634
  -3.750   0.2509   0.00912   0.00287  -0.1396   0.6854   0.0667
  -3.500   0.2764   0.00900   0.00275  -0.1390   0.6810   0.0736
  -3.250   0.3010   0.00876   0.00263  -0.1383   0.6775   0.0959
  -3.000   0.3258   0.00854   0.00252  -0.1376   0.6734   0.1200
  -2.750   0.3506   0.00838   0.00243  -0.1370   0.6689   0.1413
  -2.500   0.3755   0.00828   0.00237  -0.1363   0.6643   0.1627
  -2.250   0.4010   0.00820   0.00234  -0.1357   0.6598   0.1807
  -2.000   0.4265   0.00811   0.00230  -0.1351   0.6549   0.1962
  -1.750   0.4510   0.00805   0.00226  -0.1343   0.6487   0.2096
  -1.500   0.4753   0.00803   0.00224  -0.1334   0.6424   0.2207
  -1.250   0.5003   0.00797   0.00221  -0.1327   0.6356   0.2331
  -1.000   0.5229   0.00795   0.00219  -0.1315   0.6274   0.2477
  -0.750   0.5470   0.00791   0.00218  -0.1306   0.6194   0.2601
  -0.500   0.5689   0.00793   0.00217  -0.1292   0.6098   0.2717
  -0.250   0.5918   0.00791   0.00217  -0.1281   0.6004   0.2862
   0.000   0.6118   0.00795   0.00219  -0.1264   0.5900   0.3003
   0.250   0.6331   0.00795   0.00220  -0.1249   0.5795   0.3165
   0.500   0.6511   0.00799   0.00223  -0.1228   0.5694   0.3310
   0.750   0.6704   0.00802   0.00227  -0.1209   0.5596   0.3477
   1.000   0.6896   0.00806   0.00232  -0.1191   0.5507   0.3672
   1.250   0.7094   0.00811   0.00239  -0.1173   0.5417   0.3865
   1.500   0.7283   0.00819   0.00248  -0.1155   0.5326   0.4057
   1.750   0.7471   0.00828   0.00258  -0.1136   0.5231   0.4262
   2.000   0.7663   0.00836   0.00269  -0.1118   0.5142   0.4523
   2.250   0.7852   0.00843   0.00282  -0.1099   0.5058   0.4859
   2.500   0.8038   0.00851   0.00296  -0.1081   0.4986   0.5206
   2.750   0.8239   0.00856   0.00309  -0.1065   0.4918   0.5568
   3.000   0.8408   0.00867   0.00325  -0.1043   0.4843   0.5927
   3.250   0.8605   0.00869   0.00338  -0.1027   0.4779   0.6360
   3.500   0.9898   0.00842   0.00384  -0.1250   0.4642   0.9840
   3.750   1.0094   0.00862   0.00401  -0.1233   0.4573   1.0000
   4.000   1.0261   0.00883   0.00416  -0.1211   0.4495   1.0000
   4.250   1.0459   0.00900   0.00430  -0.1196   0.4429   1.0000
   4.500   1.0646   0.00920   0.00446  -0.1178   0.4347   1.0000
   4.750   1.0827   0.00943   0.00464  -0.1160   0.4275   1.0000
   5.000   1.1025   0.00963   0.00482  -0.1145   0.4197   1.0000
   5.250   1.1198   0.00991   0.00505  -0.1127   0.4115   1.0000
   5.500   1.1399   0.01013   0.00524  -0.1113   0.4038   1.0000
   6.000   1.1763   0.01071   0.00575  -0.1081   0.3860   1.0000
   6.250   1.1921   0.01110   0.00607  -0.1061   0.3756   1.0000
   6.500   1.2102   0.01144   0.00637  -0.1046   0.3654   1.0000
   6.750   1.2273   0.01183   0.00672  -0.1029   0.3561   1.0000
   7.000   1.2428   0.01228   0.00712  -0.1010   0.3449   1.0000
   7.250   1.2599   0.01270   0.00750  -0.0995   0.3342   1.0000
   7.500   1.2746   0.01323   0.00797  -0.0976   0.3238   1.0000
   7.750   1.2909   0.01372   0.00843  -0.0960   0.3135   1.0000
   8.000   1.3060   0.01428   0.00894  -0.0943   0.3035   1.0000
   8.500   1.3357   0.01548   0.01006  -0.0910   0.2843   1.0000
   9.000   1.3656   0.01674   0.01127  -0.0880   0.2689   1.0000
   9.250   1.3787   0.01750   0.01199  -0.0863   0.2611   1.0000
   9.500   1.3946   0.01813   0.01261  -0.0850   0.2549   1.0000
   9.750   1.4081   0.01890   0.01336  -0.0835   0.2480   1.0000
  10.000   1.4221   0.01967   0.01411  -0.0821   0.2422   1.0000
  10.250   1.4381   0.02033   0.01479  -0.0810   0.2382   1.0000
  10.500   1.4520   0.02114   0.01559  -0.0797   0.2326   1.0000
  10.750   1.4640   0.02208   0.01652  -0.0782   0.2271   1.0000
  11.000   1.4799   0.02280   0.01725  -0.0772   0.2228   1.0000
  11.250   1.4927   0.02373   0.01818  -0.0759   0.2175   1.0000
  11.500   1.5037   0.02479   0.01922  -0.0745   0.2113   1.0000
  11.750   1.5157   0.02580   0.02023  -0.0732   0.2033   1.0000
  12.000   1.5240   0.02709   0.02148  -0.0717   0.1925   1.0000
  12.250   1.5298   0.02859   0.02292  -0.0700   0.1797   1.0000
  12.500   1.5234   0.03099   0.02515  -0.0674   0.1521   1.0000
  12.750   1.5174   0.03346   0.02750  -0.0651   0.1349   1.0000
  13.000   1.5237   0.03506   0.02910  -0.0637   0.1300   1.0000
  13.250   1.5310   0.03662   0.03068  -0.0625   0.1272   1.0000
  13.500   1.5382   0.03820   0.03228  -0.0614   0.1249   1.0000
  13.750   1.5429   0.04003   0.03412  -0.0602   0.1219   1.0000
  14.000   1.5504   0.04165   0.03577  -0.0592   0.1203   1.0000
  14.250   1.5556   0.04351   0.03767  -0.0582   0.1181   1.0000
  14.500   1.5654   0.04496   0.03917  -0.0574   0.1171   1.0000
  14.750   1.5739   0.04655   0.04081  -0.0567   0.1160   1.0000
  15.000   1.5806   0.04835   0.04266  -0.0559   0.1147   1.0000
  15.250   1.5873   0.05014   0.04449  -0.0551   0.1137   1.0000
  15.500   1.5917   0.05221   0.04661  -0.0544   0.1124   1.0000
  15.750   1.5957   0.05431   0.04876  -0.0536   0.1111   1.0000
  16.000   1.5985   0.05658   0.05107  -0.0529   0.1099   1.0000
  16.250   1.5989   0.05912   0.05366  -0.0522   0.1083   1.0000
  16.500   1.5989   0.06175   0.05634  -0.0516   0.1068   1.0000
  16.750   1.6072   0.06354   0.05820  -0.0513   0.1062   1.0000
  17.000   1.6141   0.06547   0.06019  -0.0509   0.1055   1.0000
  17.250   1.6201   0.06749   0.06228  -0.0506   0.1047   1.0000
  17.500   1.6249   0.06967   0.06452  -0.0503   0.1037   1.0000
  17.750   1.6292   0.07192   0.06683  -0.0501   0.1026   1.0000
  18.000   1.6313   0.07444   0.06940  -0.0498   0.1012   1.0000
  18.250   1.6318   0.07717   0.07218  -0.0497   0.1000   1.0000
  18.500   1.6307   0.08008   0.07513  -0.0495   0.0986   1.0000
  18.750   1.6262   0.08342   0.07853  -0.0494   0.0970   1.0000
  19.000   1.6283   0.08598   0.08115  -0.0494   0.0957   1.0000
<< Back to GOE 620 AIRFOIL (goe620-il)

Polar data table (+)

Polar graphs


<< Back to GOE 620 AIRFOIL (goe620-il)