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GOE 164 (MVA MK.10) AIRFOIL (goe164-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 164 (MVA MK.10) AIRFOIL (goe164-il)
Reynolds number: 200,000
Max Cl/Cd: 77.35 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe164-il-200000-n5.txt
Download as CSV file: xf-goe164-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2685   0.11373   0.11036  -0.0269   1.0000   0.0215
  -8.750  -0.2673   0.11136   0.10803  -0.0265   1.0000   0.0218
  -8.500  -0.2669   0.10905   0.10577  -0.0260   1.0000   0.0222
  -8.250  -0.2622   0.10630   0.10306  -0.0267   0.9992   0.0226
  -8.000  -0.2447   0.10231   0.09906  -0.0313   0.9960   0.0232
  -7.750  -0.2285   0.09840   0.09516  -0.0355   0.9923   0.0235
  -7.500  -0.2141   0.09482   0.09160  -0.0439   0.9855   0.0260
  -7.250  -0.1954   0.09058   0.08738  -0.0500   0.9786   0.0262
  -7.000  -0.1752   0.08621   0.08301  -0.0554   0.9716   0.0262
  -6.500  -0.1434   0.07608   0.07287  -0.0611   0.9591   0.0175
  -6.250  -0.1190   0.07146   0.06824  -0.0675   0.9521   0.0170
  -5.750  -0.0741   0.06187   0.05861  -0.0796   0.9283   0.0163
  -5.500  -0.0477   0.05630   0.05300  -0.0870   0.9139   0.0162
  -5.250  -0.0121   0.04916   0.04577  -0.0975   0.9001   0.0163
  -5.000   0.0880   0.02266   0.01764  -0.1372   0.8945   0.0177
  -4.750   0.1284   0.01955   0.01382  -0.1410   0.8844   0.0185
  -4.500   0.1686   0.01739   0.01127  -0.1441   0.8740   0.0198
  -4.250   0.2119   0.01635   0.01003  -0.1475   0.8635   0.0222
  -4.000   0.2559   0.01530   0.00867  -0.1507   0.8521   0.0256
  -3.750   0.2994   0.01419   0.00734  -0.1539   0.8386   0.0288
  -3.500   0.3397   0.01364   0.00658  -0.1563   0.8221   0.0347
  -3.250   0.3755   0.01301   0.00573  -0.1579   0.8057   0.0408
  -3.000   0.4077   0.01271   0.00520  -0.1585   0.7893   0.0484
  -2.750   0.4379   0.01231   0.00461  -0.1589   0.7723   0.0594
  -2.500   0.4666   0.01195   0.00421  -0.1590   0.7552   0.0812
  -2.250   0.4942   0.01195   0.00424  -0.1587   0.7382   0.1340
  -2.000   0.5214   0.01211   0.00423  -0.1582   0.7226   0.1514
  -1.750   0.5483   0.01224   0.00420  -0.1578   0.7075   0.1627
  -1.500   0.5750   0.01242   0.00419  -0.1573   0.6925   0.1741
  -1.250   0.6014   0.01250   0.00420  -0.1568   0.6774   0.1808
  -1.000   0.6278   0.01261   0.00413  -0.1563   0.6616   0.1886
  -0.750   0.6539   0.01266   0.00413  -0.1557   0.6455   0.1955
  -0.500   0.6801   0.01269   0.00404  -0.1552   0.6296   0.2002
  -0.250   0.7062   0.01272   0.00393  -0.1547   0.6135   0.2036
   0.000   0.7320   0.01272   0.00388  -0.1541   0.5977   0.2071
   0.250   0.7576   0.01277   0.00385  -0.1536   0.5808   0.2111
   0.500   0.7830   0.01286   0.00382  -0.1529   0.5621   0.2151
   0.750   0.8080   0.01297   0.00381  -0.1522   0.5418   0.2189
   1.000   0.8327   0.01309   0.00385  -0.1515   0.5214   0.2229
   1.250   0.8575   0.01323   0.00390  -0.1508   0.5005   0.2277
   1.750   0.9066   0.01357   0.00407  -0.1495   0.4573   0.2398
   2.000   0.9314   0.01375   0.00418  -0.1488   0.4372   0.2471
   2.250   0.9559   0.01392   0.00432  -0.1482   0.4190   0.2547
   2.500   0.9804   0.01412   0.00448  -0.1475   0.4024   0.2646
   3.000   1.0294   0.01451   0.00489  -0.1463   0.3755   0.3027
   3.250   1.0535   0.01471   0.00513  -0.1456   0.3641   0.3452
   3.500   1.0776   0.01489   0.00538  -0.1449   0.3544   0.4039
   3.750   1.0976   0.01422   0.00558  -0.1432   0.3467   1.0000
   4.000   1.1216   0.01454   0.00583  -0.1425   0.3387   1.0000
   4.250   1.1462   0.01482   0.00609  -0.1419   0.3313   1.0000
   4.500   1.1701   0.01515   0.00637  -0.1412   0.3239   1.0000
   4.750   1.1943   0.01544   0.00665  -0.1405   0.3165   1.0000
   5.000   1.2178   0.01578   0.00697  -0.1398   0.3087   1.0000
   5.250   1.2418   0.01608   0.00728  -0.1391   0.3019   1.0000
   5.500   1.2654   0.01639   0.00761  -0.1383   0.2946   1.0000
   5.750   1.2888   0.01671   0.00795  -0.1376   0.2877   1.0000
   6.000   1.3123   0.01702   0.00831  -0.1368   0.2802   1.0000
   6.250   1.3354   0.01735   0.00868  -0.1360   0.2733   1.0000
   6.500   1.3584   0.01767   0.00905  -0.1352   0.2652   1.0000
   6.750   1.3810   0.01802   0.00945  -0.1343   0.2571   1.0000
   7.000   1.4028   0.01839   0.00988  -0.1333   0.2480   1.0000
   7.250   1.4248   0.01876   0.01031  -0.1323   0.2380   1.0000
   7.500   1.4448   0.01922   0.01077  -0.1311   0.2228   1.0000
   7.750   1.4610   0.01992   0.01134  -0.1293   0.1986   1.0000
   8.250   1.4902   0.02152   0.01282  -0.1252   0.1701   1.0000
   8.500   1.5041   0.02226   0.01358  -0.1230   0.1599   1.0000
   8.750   1.5169   0.02309   0.01441  -0.1207   0.1473   1.0000
   9.000   1.5325   0.02375   0.01512  -0.1189   0.1269   1.0000
   9.250   1.5304   0.02559   0.01658  -0.1148   0.0834   1.0000
   9.500   1.5356   0.02696   0.01799  -0.1116   0.0719   1.0000
   9.750   1.5377   0.02858   0.01952  -0.1083   0.0345   1.0000
  10.000   1.5362   0.03054   0.02141  -0.1046   0.0219   1.0000
  10.250   1.5385   0.03226   0.02323  -0.1017   0.0180   1.0000
  10.500   1.5431   0.03386   0.02501  -0.0992   0.0161   1.0000
  10.750   1.5468   0.03558   0.02690  -0.0969   0.0147   1.0000
  11.000   1.5484   0.03758   0.02907  -0.0947   0.0137   1.0000
  11.250   1.5475   0.03993   0.03159  -0.0926   0.0130   1.0000
  11.500   1.5438   0.04272   0.03456  -0.0908   0.0123   1.0000
  11.750   1.5368   0.04605   0.03808  -0.0893   0.0119   1.0000
  12.000   1.5285   0.04972   0.04194  -0.0882   0.0115   1.0000
  12.250   1.5244   0.05307   0.04546  -0.0875   0.0112   1.0000
  12.500   1.5188   0.05673   0.04929  -0.0871   0.0108   1.0000
  12.750   1.5119   0.06072   0.05344  -0.0869   0.0104   1.0000
  13.000   1.5038   0.06501   0.05790  -0.0870   0.0101   1.0000
  13.250   1.4946   0.06960   0.06264  -0.0874   0.0098   1.0000
  13.500   1.4850   0.07440   0.06759  -0.0880   0.0095   1.0000
  13.750   1.4746   0.07945   0.07279  -0.0888   0.0093   1.0000
  14.000   1.4638   0.08465   0.07813  -0.0898   0.0092   1.0000
  14.250   1.4529   0.08998   0.08359  -0.0910   0.0090   1.0000
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