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GOE 164 (MVA MK.10) AIRFOIL (goe164-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 164 (MVA MK.10) AIRFOIL (goe164-il)
Reynolds number: 500,000
Max Cl/Cd: 104.57 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe164-il-500000.txt
Download as CSV file: xf-goe164-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 164 (MVA MK.10) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3033   0.11238   0.11020  -0.0248   1.0000   0.0175
  -9.000  -0.3054   0.10973   0.10758  -0.0252   1.0000   0.0176
  -8.250  -0.3100   0.10099   0.09893  -0.0234   1.0000   0.0181
  -8.000  -0.3066   0.09906   0.09702  -0.0218   1.0000   0.0184
  -7.750  -0.2860   0.09576   0.09372  -0.0254   0.9979   0.0189
  -7.500  -0.2649   0.09212   0.09008  -0.0303   0.9953   0.0196
  -7.250  -0.2464   0.08834   0.08630  -0.0351   0.9916   0.0206
  -7.000  -0.2148   0.08184   0.07980  -0.0487   0.9857   0.0227
  -6.750  -0.1855   0.07643   0.07437  -0.0581   0.9805   0.0229
  -6.500  -0.1662   0.07101   0.06896  -0.0632   0.9763   0.0236
  -6.250  -0.1354   0.06776   0.06569  -0.0684   0.9737   0.0243
  -6.000  -0.1060   0.06409   0.06200  -0.0744   0.9689   0.0252
  -5.750  -0.0042   0.02103   0.01732  -0.1356   0.9603   0.0183
  -5.500   0.0302   0.01848   0.01442  -0.1383   0.9552   0.0188
  -5.250   0.0645   0.01696   0.01269  -0.1402   0.9498   0.0196
  -5.000   0.1039   0.01583   0.01136  -0.1427   0.9466   0.0211
  -4.750   0.1329   0.01454   0.00980  -0.1429   0.9368   0.0221
  -4.500   0.1707   0.01328   0.00828  -0.1448   0.9314   0.0231
  -4.000   0.2375   0.01114   0.00591  -0.1470   0.8985   0.0268
  -3.750   0.2861   0.01054   0.00512  -0.1510   0.8745   0.0299
  -3.500   0.3263   0.00971   0.00405  -0.1535   0.8401   0.0340
  -3.250   0.3561   0.00960   0.00368  -0.1535   0.8109   0.0376
  -3.000   0.3835   0.00924   0.00314  -0.1533   0.7884   0.0437
  -2.750   0.4105   0.00914   0.00288  -0.1528   0.7708   0.0488
  -2.500   0.4376   0.00887   0.00250  -0.1525   0.7555   0.0593
  -2.250   0.4646   0.00852   0.00232  -0.1523   0.7416   0.1212
  -2.000   0.4916   0.00869   0.00245  -0.1518   0.7279   0.1528
  -1.750   0.5184   0.00885   0.00253  -0.1513   0.7139   0.1635
  -1.500   0.5452   0.00904   0.00258  -0.1508   0.6989   0.1706
  -1.250   0.5717   0.00910   0.00260  -0.1503   0.6834   0.1776
  -1.000   0.5983   0.00921   0.00261  -0.1499   0.6684   0.1833
  -0.750   0.6248   0.00923   0.00254  -0.1494   0.6528   0.1873
  -0.500   0.6509   0.00929   0.00254  -0.1489   0.6348   0.1922
  -0.250   0.6769   0.00945   0.00258  -0.1483   0.6137   0.1987
   0.000   0.7024   0.00949   0.00251  -0.1477   0.5907   0.2032
   0.250   0.7281   0.00956   0.00250  -0.1471   0.5689   0.2065
   0.500   0.7540   0.00966   0.00250  -0.1466   0.5486   0.2102
   0.750   0.7799   0.00980   0.00252  -0.1460   0.5295   0.2141
   1.000   0.8056   0.00987   0.00253  -0.1455   0.5085   0.2186
   1.250   0.8313   0.01000   0.00258  -0.1450   0.4858   0.2231
   1.500   0.8569   0.01016   0.00264  -0.1445   0.4633   0.2278
   1.750   0.8822   0.01033   0.00271  -0.1439   0.4369   0.2330
   2.000   0.9074   0.01052   0.00280  -0.1434   0.4102   0.2390
   2.250   0.9327   0.01073   0.00292  -0.1429   0.3888   0.2459
   2.500   0.9582   0.01090   0.00306  -0.1424   0.3725   0.2554
   2.750   0.9838   0.01107   0.00321  -0.1420   0.3600   0.2672
   3.000   1.0095   0.01123   0.00338  -0.1416   0.3494   0.2870
   3.250   1.0356   0.01132   0.00359  -0.1412   0.3405   0.3399
   3.500   1.0614   0.01129   0.00385  -0.1410   0.3324   0.4758
   3.750   1.0824   0.01060   0.00401  -0.1395   0.3256   1.0000
   4.000   1.1077   0.01085   0.00419  -0.1390   0.3182   1.0000
   4.250   1.1338   0.01102   0.00436  -0.1386   0.3122   1.0000
   4.500   1.1593   0.01125   0.00455  -0.1381   0.3052   1.0000
   4.750   1.1850   0.01145   0.00474  -0.1377   0.2992   1.0000
   5.000   1.2106   0.01164   0.00493  -0.1372   0.2924   1.0000
   5.250   1.2357   0.01187   0.00515  -0.1367   0.2857   1.0000
   5.500   1.2613   0.01207   0.00536  -0.1363   0.2778   1.0000
   5.750   1.2862   0.01230   0.00558  -0.1357   0.2696   1.0000
   6.000   1.3108   0.01256   0.00581  -0.1351   0.2580   1.0000
   6.250   1.3346   0.01288   0.00606  -0.1345   0.2360   1.0000
   6.750   1.3770   0.01397   0.00684  -0.1323   0.1867   1.0000
   7.000   1.3980   0.01450   0.00730  -0.1312   0.1748   1.0000
   7.250   1.4204   0.01490   0.00771  -0.1303   0.1680   1.0000
   7.500   1.4415   0.01539   0.00818  -0.1292   0.1608   1.0000
   7.750   1.4644   0.01571   0.00855  -0.1284   0.1543   1.0000
   8.000   1.4851   0.01621   0.00902  -0.1272   0.1451   1.0000
   8.250   1.5064   0.01663   0.00944  -0.1262   0.1307   1.0000
   8.500   1.5176   0.01787   0.01036  -0.1236   0.0832   1.0000
   8.750   1.5331   0.01871   0.01121  -0.1217   0.0703   1.0000
   9.000   1.5383   0.02024   0.01245  -0.1181   0.0276   1.0000
   9.250   1.5475   0.02130   0.01353  -0.1149   0.0211   1.0000
   9.500   1.5602   0.02210   0.01445  -0.1124   0.0191   1.0000
   9.750   1.5711   0.02301   0.01544  -0.1098   0.0176   1.0000
  10.000   1.5782   0.02416   0.01668  -0.1066   0.0161   1.0000
  10.250   1.5809   0.02561   0.01827  -0.1030   0.0151   1.0000
  10.500   1.5892   0.02670   0.01946  -0.1004   0.0146   1.0000
  10.750   1.5950   0.02800   0.02087  -0.0975   0.0140   1.0000
  11.000   1.5987   0.02949   0.02247  -0.0947   0.0135   1.0000
  11.250   1.6007   0.03119   0.02429  -0.0919   0.0130   1.0000
  11.500   1.6007   0.03316   0.02637  -0.0893   0.0127   1.0000
  11.750   1.5987   0.03547   0.02880  -0.0870   0.0123   1.0000
  12.000   1.5937   0.03828   0.03172  -0.0851   0.0120   1.0000
  12.250   1.5853   0.04168   0.03526  -0.0835   0.0117   1.0000
  12.500   1.5725   0.04582   0.03954  -0.0822   0.0114   1.0000
  12.750   1.5563   0.05056   0.04443  -0.0813   0.0112   1.0000
  13.000   1.5543   0.05381   0.04780  -0.0810   0.0110   1.0000
  13.250   1.5528   0.05708   0.05119  -0.0808   0.0108   1.0000
  13.500   1.5489   0.06075   0.05498  -0.0807   0.0106   1.0000
  13.750   1.5432   0.06473   0.05908  -0.0808   0.0104   1.0000
  14.000   1.5366   0.06889   0.06335  -0.0810   0.0102   1.0000
  14.250   1.5297   0.07313   0.06770  -0.0813   0.0101   1.0000
  14.500   1.5234   0.07736   0.07204  -0.0816   0.0099   1.0000
  14.750   1.5175   0.08160   0.07637  -0.0821   0.0098   1.0000
  15.000   1.5118   0.08578   0.08067  -0.0825   0.0096   1.0000
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