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GOE 223 (MVA H.34) AIRFOIL (goe223-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 223 (MVA H.34) AIRFOIL (goe223-il)
Reynolds number: 200,000
Max Cl/Cd: 72.97 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe223-il-200000.txt
Download as CSV file: xf-goe223-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 223 (MVA H.34) 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.1160   0.10437   0.10092  -0.1015   0.9621   0.0857
 -11.250  -0.0888   0.10297   0.09949  -0.1013   0.9580   0.0886
 -11.000  -0.0822   0.09946   0.09596  -0.1041   0.9521   0.0938
 -10.750  -0.1063   0.09178   0.08834  -0.1108   0.9435   0.0988
 -10.500  -0.0844   0.09070   0.08722  -0.1088   0.9377   0.1005
 -10.250  -0.0737   0.08872   0.08524  -0.1083   0.9299   0.1029
 -10.000  -0.1310   0.07685   0.07345  -0.1206   0.9197   0.1130
  -9.750  -0.1062   0.07684   0.07341  -0.1168   0.9140   0.1142
  -9.500  -0.2913   0.04346   0.03817  -0.1522   0.8907   0.0622
  -9.250  -0.2761   0.03905   0.03382  -0.1516   0.8844   0.0588
  -9.000  -0.2640   0.03460   0.02840  -0.1530   0.8788   0.0534
  -8.750  -0.2415   0.03220   0.02577  -0.1533   0.8748   0.0536
  -8.500  -0.2220   0.03032   0.02376  -0.1529   0.8676   0.0540
  -8.250  -0.1967   0.02856   0.02182  -0.1529   0.8632   0.0542
  -8.000  -0.1695   0.02695   0.02004  -0.1530   0.8598   0.0543
  -7.750  -0.1479   0.02584   0.01887  -0.1523   0.8525   0.0546
  -7.500  -0.1221   0.02470   0.01769  -0.1521   0.8475   0.0557
  -7.250  -0.0943   0.02366   0.01658  -0.1521   0.8438   0.0570
  -7.000  -0.0714   0.02290   0.01579  -0.1514   0.8363   0.0578
  -6.750  -0.0451   0.02200   0.01484  -0.1511   0.8307   0.0585
  -6.500  -0.0170   0.02113   0.01390  -0.1510   0.8262   0.0594
  -6.250   0.0066   0.02053   0.01329  -0.1505   0.8176   0.0604
  -6.000   0.0353   0.01985   0.01251  -0.1507   0.8120   0.0619
  -5.750   0.0609   0.01902   0.01171  -0.1509   0.8046   0.0638
  -5.500   0.0891   0.01831   0.01097  -0.1514   0.7974   0.0658
  -5.250   0.1189   0.01771   0.01027  -0.1521   0.7910   0.0682
  -5.000   0.1469   0.01722   0.00970  -0.1524   0.7819   0.0712
  -4.750   0.1778   0.01661   0.00899  -0.1532   0.7752   0.0770
  -4.500   0.2058   0.01610   0.00848  -0.1536   0.7648   0.0901
  -4.250   0.2362   0.01438   0.00759  -0.1559   0.7563   0.3057
  -4.000   0.2654   0.01448   0.00763  -0.1558   0.7460   0.3607
  -3.750   0.2934   0.01471   0.00781  -0.1555   0.7350   0.3833
  -3.500   0.3229   0.01492   0.00789  -0.1553   0.7258   0.4002
  -3.250   0.3504   0.01512   0.00798  -0.1550   0.7134   0.4136
  -3.000   0.3777   0.01531   0.00817  -0.1546   0.7019   0.4228
  -2.750   0.4068   0.01538   0.00805  -0.1547   0.6920   0.4318
  -2.500   0.4339   0.01546   0.00811  -0.1544   0.6806   0.4377
  -2.250   0.4623   0.01560   0.00808  -0.1545   0.6700   0.4467
  -2.000   0.4900   0.01576   0.00820  -0.1541   0.6614   0.4546
  -1.750   0.5173   0.01592   0.00827  -0.1541   0.6509   0.4636
  -1.500   0.5444   0.01610   0.00844  -0.1537   0.6428   0.4719
  -1.250   0.5720   0.01627   0.00852  -0.1536   0.6339   0.4812
  -1.000   0.6001   0.01629   0.00846  -0.1537   0.6270   0.4862
  -0.750   0.6274   0.01630   0.00843  -0.1537   0.6190   0.4897
  -0.250   0.6844   0.01636   0.00825  -0.1543   0.6051   0.4986
   0.000   0.7129   0.01634   0.00813  -0.1546   0.5988   0.5019
   0.250   0.7404   0.01639   0.00816  -0.1547   0.5924   0.5052
   0.500   0.7678   0.01645   0.00818  -0.1548   0.5858   0.5093
   0.750   0.7974   0.01655   0.00813  -0.1553   0.5807   0.5142
   1.000   0.8248   0.01663   0.00819  -0.1555   0.5752   0.5185
   1.250   0.8519   0.01669   0.00826  -0.1555   0.5698   0.5219
   1.500   0.8808   0.01681   0.00830  -0.1558   0.5649   0.5261
   1.750   0.9081   0.01695   0.00842  -0.1560   0.5600   0.5312
   2.000   0.9354   0.01705   0.00852  -0.1561   0.5549   0.5362
   2.250   0.9631   0.01717   0.00863  -0.1562   0.5504   0.5405
   2.500   0.9919   0.01735   0.00876  -0.1566   0.5462   0.5455
   2.750   1.0182   0.01750   0.00894  -0.1566   0.5418   0.5511
   3.000   1.0450   0.01762   0.00911  -0.1566   0.5374   0.5559
   3.250   1.0728   0.01779   0.00927  -0.1568   0.5333   0.5617
   3.500   1.1012   0.01802   0.00944  -0.1572   0.5291   0.5686
   3.750   1.1252   0.01814   0.00968  -0.1567   0.5238   0.5740
   4.000   1.1514   0.01828   0.00986  -0.1566   0.5187   0.5804
   4.250   1.1801   0.01849   0.01000  -0.1570   0.5148   0.5879
   4.500   1.2054   0.01869   0.01031  -0.1568   0.5110   0.5946
   4.750   1.2296   0.01888   0.01059  -0.1564   0.5062   0.6035
   5.000   1.2549   0.01902   0.01079  -0.1561   0.5013   0.6113
   5.500   1.3051   0.01943   0.01131  -0.1557   0.4925   0.6301
   5.750   1.3280   0.01960   0.01158  -0.1551   0.4872   0.6409
   6.000   1.3532   0.01976   0.01179  -0.1548   0.4828   0.6530
   6.250   1.3793   0.01996   0.01203  -0.1547   0.4787   0.6660
   6.500   1.3988   0.02015   0.01242  -0.1536   0.4738   0.6801
   6.750   1.4206   0.02031   0.01269  -0.1528   0.4688   0.6964
   7.000   1.4448   0.02043   0.01287  -0.1523   0.4643   0.7153
   7.250   1.4646   0.02062   0.01323  -0.1512   0.4593   0.7375
   7.500   1.4820   0.02074   0.01356  -0.1497   0.4537   0.7652
   7.750   1.4999   0.02071   0.01374  -0.1480   0.4487   0.8228
   8.000   1.5155   0.02077   0.01397  -0.1460   0.4435   1.0000
   8.250   1.5278   0.02113   0.01441  -0.1438   0.4366   1.0000
   8.500   1.5430   0.02144   0.01467  -0.1420   0.4294   1.0000
   8.750   1.5509   0.02197   0.01533  -0.1393   0.4200   1.0000
   9.000   1.5605   0.02252   0.01589  -0.1369   0.4102   1.0000
   9.250   1.5681   0.02320   0.01658  -0.1343   0.3987   1.0000
   9.500   1.5748   0.02406   0.01749  -0.1318   0.3853   1.0000
   9.750   1.5810   0.02505   0.01849  -0.1295   0.3706   1.0000
  10.000   1.5846   0.02628   0.01969  -0.1270   0.3536   1.0000
  10.250   1.5858   0.02779   0.02114  -0.1244   0.3342   1.0000
  10.500   1.5838   0.02963   0.02291  -0.1217   0.3140   1.0000
  10.750   1.5802   0.03174   0.02493  -0.1191   0.2965   1.0000
  11.000   1.5772   0.03393   0.02705  -0.1167   0.2828   1.0000
  11.250   1.5746   0.03618   0.02927  -0.1146   0.2719   1.0000
  11.500   1.5719   0.03855   0.03160  -0.1125   0.2625   1.0000
  11.750   1.5729   0.04072   0.03379  -0.1109   0.2544   1.0000
  12.000   1.5698   0.04331   0.03635  -0.1092   0.2465   1.0000
  12.250   1.5699   0.04572   0.03881  -0.1078   0.2379   1.0000
  12.500   1.5667   0.04848   0.04155  -0.1064   0.2308   1.0000
  12.750   1.5695   0.05081   0.04396  -0.1054   0.2237   1.0000
  13.000   1.5672   0.05367   0.04683  -0.1043   0.2167   1.0000
  13.250   1.5687   0.05624   0.04948  -0.1035   0.2098   1.0000
  13.500   1.5663   0.05928   0.05256  -0.1027   0.2021   1.0000
  13.750   1.5654   0.06229   0.05565  -0.1021   0.1930   1.0000
  14.000   1.5612   0.06573   0.05912  -0.1015   0.1839   1.0000
  14.250   1.5601   0.06893   0.06240  -0.1012   0.1696   1.0000
  14.500   1.5492   0.07333   0.06674  -0.1009   0.1446   1.0000
  14.750   1.5308   0.07873   0.07200  -0.1007   0.1319   1.0000
  15.000   1.5183   0.08342   0.07664  -0.1005   0.1251   1.0000
  15.250   1.5070   0.08796   0.08119  -0.1004   0.1190   1.0000
  15.500   1.4985   0.09219   0.08545  -0.1003   0.1132   1.0000
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