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GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 190 (MVA MK.18) AIRFOIL (goe190-il)
Reynolds number: 500,000
Max Cl/Cd: 100.72 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe190-il-500000.txt
Download as CSV file: xf-goe190-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 190 (MVA MK.18) AIRFOIL                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2464   0.10146   0.09931  -0.0425   0.9949   0.0362
 -10.250  -0.2297   0.09851   0.09636  -0.0447   0.9938   0.0369
 -10.000  -0.6038   0.04472   0.04191  -0.0835   0.9869   0.0266
  -9.750  -0.5661   0.03852   0.03546  -0.0989   0.9836   0.0276
  -9.500  -0.5291   0.03099   0.02730  -0.1147   0.9787   0.0290
  -9.250  -0.4967   0.02707   0.02290  -0.1212   0.9747   0.0301
  -9.000  -0.4614   0.02586   0.02166  -0.1241   0.9725   0.0310
  -8.750  -0.4240   0.02500   0.02074  -0.1271   0.9709   0.0319
  -8.500  -0.3857   0.02395   0.01954  -0.1303   0.9696   0.0332
  -8.250  -0.3616   0.02282   0.01822  -0.1304   0.9636   0.0344
  -8.000  -0.3271   0.02121   0.01635  -0.1328   0.9603   0.0356
  -7.750  -0.2906   0.02001   0.01512  -0.1352   0.9581   0.0368
  -7.500  -0.2513   0.01932   0.01438  -0.1379   0.9564   0.0380
  -7.250  -0.2110   0.01861   0.01359  -0.1406   0.9552   0.0396
  -7.000  -0.1891   0.01795   0.01283  -0.1394   0.9479   0.0407
  -6.750  -0.1531   0.01740   0.01213  -0.1410   0.9448   0.0415
  -6.500  -0.1180   0.01585   0.01058  -0.1429   0.9427   0.0432
  -6.250  -0.0779   0.01519   0.00992  -0.1455   0.9411   0.0448
  -6.000  -0.0510   0.01461   0.00930  -0.1451   0.9348   0.0461
  -5.750  -0.0187   0.01398   0.00863  -0.1459   0.9297   0.0474
  -5.500   0.0201   0.01347   0.00805  -0.1479   0.9268   0.0489
  -5.250   0.0418   0.01270   0.00725  -0.1465   0.9169   0.0502
  -5.000   0.0749   0.01193   0.00647  -0.1475   0.9099   0.0521
  -4.750   0.0913   0.01148   0.00599  -0.1448   0.8903   0.0535
  -4.500   0.1291   0.01095   0.00541  -0.1466   0.8746   0.0557
  -4.250   0.1764   0.01050   0.00484  -0.1503   0.8556   0.0582
  -4.000   0.2200   0.00984   0.00400  -0.1534   0.8270   0.0622
  -3.750   0.2522   0.00967   0.00359  -0.1541   0.7985   0.0659
  -3.500   0.2795   0.00962   0.00335  -0.1537   0.7759   0.0691
  -3.250   0.3052   0.00942   0.00302  -0.1531   0.7563   0.0767
  -3.000   0.3306   0.00923   0.00274  -0.1524   0.7390   0.0922
  -2.750   0.3543   0.00855   0.00251  -0.1520   0.7242   0.2506
  -2.500   0.3805   0.00868   0.00257  -0.1513   0.7102   0.2752
  -2.250   0.4066   0.00883   0.00264  -0.1506   0.6959   0.2881
  -2.000   0.4322   0.00895   0.00270  -0.1499   0.6808   0.2968
  -1.750   0.4578   0.00910   0.00274  -0.1491   0.6645   0.3049
  -1.500   0.4830   0.00917   0.00277  -0.1482   0.6465   0.3112
  -1.250   0.5081   0.00929   0.00281  -0.1474   0.6269   0.3168
  -1.000   0.5331   0.00944   0.00283  -0.1465   0.6073   0.3221
  -0.750   0.5579   0.00955   0.00288  -0.1457   0.5905   0.3281
  -0.500   0.5832   0.00971   0.00296  -0.1449   0.5774   0.3333
   0.000   0.6351   0.00996   0.00305  -0.1437   0.5571   0.3425
   0.250   0.6608   0.01011   0.00314  -0.1430   0.5487   0.3466
   0.500   0.6876   0.01019   0.00321  -0.1426   0.5413   0.3504
   0.750   0.7139   0.01031   0.00326  -0.1421   0.5346   0.3535
   1.000   0.7407   0.01040   0.00331  -0.1417   0.5287   0.3561
   1.250   0.7673   0.01043   0.00333  -0.1413   0.5226   0.3590
   1.500   0.7935   0.01055   0.00342  -0.1408   0.5165   0.3619
   1.750   0.8201   0.01061   0.00350  -0.1403   0.5107   0.3649
   2.000   0.8465   0.01070   0.00359  -0.1399   0.5048   0.3684
   2.250   0.8728   0.01086   0.00369  -0.1394   0.4992   0.3721
   2.500   0.8992   0.01091   0.00376  -0.1390   0.4937   0.3754
   2.750   0.9249   0.01096   0.00385  -0.1384   0.4870   0.3789
   3.000   0.9504   0.01112   0.00397  -0.1377   0.4799   0.3824
   3.250   0.9760   0.01115   0.00405  -0.1371   0.4729   0.3863
   3.500   1.0014   0.01127   0.00414  -0.1365   0.4664   0.3902
   3.750   1.0267   0.01133   0.00424  -0.1358   0.4596   0.3941
   4.000   1.0515   0.01140   0.00435  -0.1350   0.4517   0.3982
   4.250   1.0762   0.01152   0.00447  -0.1343   0.4440   0.4030
   4.500   1.1010   0.01162   0.00457  -0.1335   0.4359   0.4077
   4.750   1.1251   0.01173   0.00471  -0.1327   0.4287   0.4123
   5.000   1.1498   0.01182   0.00486  -0.1319   0.4205   0.4171
   5.250   1.1734   0.01198   0.00500  -0.1309   0.4128   0.4223
   5.500   1.1976   0.01208   0.00515  -0.1301   0.4040   0.4271
   5.750   1.2206   0.01225   0.00533  -0.1291   0.3956   0.4323
   6.000   1.2436   0.01241   0.00550  -0.1280   0.3858   0.4380
   6.250   1.2662   0.01259   0.00570  -0.1269   0.3764   0.4435
   6.500   1.2876   0.01282   0.00592  -0.1256   0.3670   0.4494
   6.750   1.3104   0.01301   0.00614  -0.1246   0.3577   0.4558
   7.000   1.3308   0.01325   0.00639  -0.1231   0.3487   0.4614
   7.250   1.3519   0.01346   0.00663  -0.1218   0.3398   0.4677
   7.500   1.3715   0.01371   0.00689  -0.1202   0.3308   0.4739
   7.750   1.3908   0.01395   0.00716  -0.1185   0.3217   0.4801
   8.000   1.4108   0.01421   0.00745  -0.1170   0.3138   0.4873
   8.250   1.4292   0.01450   0.00777  -0.1152   0.3048   0.4945
   8.500   1.4489   0.01476   0.00808  -0.1137   0.2960   0.5024
   8.750   1.4660   0.01511   0.00844  -0.1117   0.2858   0.5100
   9.000   1.4837   0.01544   0.00879  -0.1099   0.2733   0.5186
   9.250   1.5003   0.01580   0.00918  -0.1080   0.2586   0.5278
   9.500   1.5160   0.01622   0.00960  -0.1059   0.2434   0.5392
   9.750   1.5294   0.01674   0.01010  -0.1035   0.2260   0.5538
  10.000   1.5424   0.01728   0.01068  -0.1012   0.2079   0.5832
  10.250   1.5843   0.01789   0.01169  -0.1055   0.1835   1.0000
  10.500   1.5960   0.01863   0.01238  -0.1031   0.1709   1.0000
  10.750   1.6079   0.01937   0.01310  -0.1007   0.1603   1.0000
  11.000   1.6181   0.02022   0.01392  -0.0982   0.1498   1.0000
  11.250   1.6275   0.02112   0.01478  -0.0956   0.1387   1.0000
  11.500   1.6378   0.02199   0.01564  -0.0933   0.1272   1.0000
  11.750   1.6458   0.02301   0.01664  -0.0908   0.1149   1.0000
  12.000   1.6510   0.02425   0.01782  -0.0881   0.1016   1.0000
  12.250   1.6550   0.02560   0.01914  -0.0854   0.0908   1.0000
  12.500   1.6582   0.02708   0.02061  -0.0828   0.0821   1.0000
  12.750   1.6596   0.02877   0.02229  -0.0803   0.0749   1.0000
  13.000   1.6626   0.03045   0.02400  -0.0782   0.0685   1.0000
  13.250   1.6640   0.03236   0.02595  -0.0763   0.0626   1.0000
  13.500   1.6632   0.03460   0.02820  -0.0745   0.0564   1.0000
  13.750   1.6630   0.03692   0.03056  -0.0731   0.0499   1.0000
  14.000   1.6593   0.03971   0.03338  -0.0718   0.0436   1.0000
  14.250   1.6535   0.04285   0.03654  -0.0707   0.0382   1.0000
  14.500   1.6458   0.04633   0.04006  -0.0698   0.0337   1.0000
  14.750   1.6397   0.04977   0.04357  -0.0692   0.0305   1.0000
  15.000   1.6309   0.05365   0.04751  -0.0688   0.0284   1.0000
  15.250   1.6239   0.05749   0.05144  -0.0687   0.0266   1.0000
  15.500   1.6162   0.06152   0.05558  -0.0688   0.0252   1.0000
  15.750   1.6065   0.06592   0.06006  -0.0691   0.0241   1.0000
  16.000   1.5942   0.07082   0.06505  -0.0697   0.0233   1.0000
  16.250   1.5850   0.07537   0.06971  -0.0703   0.0225   1.0000
  16.500   1.5770   0.07980   0.07425  -0.0710   0.0218   1.0000
  16.750   1.5677   0.08448   0.07904  -0.0718   0.0212   1.0000
  17.000   1.5582   0.08928   0.08395  -0.0728   0.0207   1.0000
  17.250   1.5473   0.09436   0.08912  -0.0740   0.0202   1.0000
  17.500   1.5356   0.09966   0.09451  -0.0754   0.0198   1.0000
  17.750   1.5214   0.10550   0.10043  -0.0771   0.0193   1.0000
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