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GOE 124 (MVA H.4) AIRFOIL (goe124-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 124 (MVA H.4) AIRFOIL (goe124-il)
Reynolds number: 200,000
Max Cl/Cd: 83.78 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe124-il-200000-n5.txt
Download as CSV file: xf-goe124-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 124 (MVA H.4) 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3353   0.12001   0.11642  -0.0179   1.0000   0.0241
  -9.750  -0.3321   0.11750   0.11395  -0.0209   1.0000   0.0243
  -9.500  -0.3282   0.11469   0.11116  -0.0235   1.0000   0.0243
  -9.250  -0.3232   0.11159   0.10810  -0.0258   1.0000   0.0244
  -9.000  -0.3117   0.10692   0.10345  -0.0252   1.0000   0.0246
  -8.750  -0.3010   0.10331   0.09985  -0.0248   1.0000   0.0250
  -8.500  -0.2927   0.10035   0.09693  -0.0256   1.0000   0.0254
  -8.250  -0.2853   0.09758   0.09418  -0.0266   1.0000   0.0259
  -8.000  -0.2785   0.09499   0.09164  -0.0277   1.0000   0.0269
  -7.750  -0.2686   0.09214   0.08881  -0.0304   0.9868   0.0286
  -7.500  -0.2492   0.08877   0.08543  -0.0401   0.9582   0.0301
  -7.250  -0.2262   0.08470   0.08131  -0.0496   0.9382   0.0303
  -7.000  -0.2040   0.08058   0.07712  -0.0566   0.9213   0.0305
  -6.500  -0.1783   0.07266   0.06915  -0.0589   0.8938   0.0312
  -6.250  -0.1657   0.07003   0.06648  -0.0584   0.8809   0.0320
  -6.000  -0.1482   0.06712   0.06350  -0.0607   0.8680   0.0328
  -5.750  -0.1276   0.06398   0.06028  -0.0642   0.8554   0.0338
  -5.500  -0.1038   0.06069   0.05690  -0.0686   0.8432   0.0353
  -5.250  -0.0507   0.05615   0.05205  -0.0826   0.8316   0.0387
  -5.000  -0.0164   0.05228   0.04791  -0.0883   0.8215   0.0389
  -4.750   0.0021   0.04780   0.04340  -0.0901   0.8113   0.0395
  -4.500   0.0218   0.04520   0.04073  -0.0908   0.8013   0.0402
  -4.000   0.0736   0.04036   0.03567  -0.0945   0.7822   0.0423
  -3.750   0.1212   0.03773   0.03249  -0.1001   0.7739   0.0488
  -3.500   0.1545   0.03537   0.02974  -0.1024   0.7649   0.0490
  -3.250   0.1788   0.03142   0.02579  -0.1042   0.7563   0.0501
  -3.000   0.2060   0.02948   0.02373  -0.1052   0.7467   0.0511
  -2.750   0.2352   0.02770   0.02178  -0.1064   0.7362   0.0523
  -2.500   0.2691   0.02504   0.01872  -0.1078   0.7264   0.0444
  -2.250   0.3009   0.02319   0.01653  -0.1088   0.7156   0.0441
  -1.750   0.3666   0.01985   0.01225  -0.1099   0.6951   0.0383
  -1.500   0.3966   0.01865   0.01079  -0.1105   0.6860   0.0380
  -1.250   0.4265   0.01770   0.00960  -0.1108   0.6782   0.0380
  -1.000   0.4561   0.01692   0.00860  -0.1111   0.6699   0.0380
  -0.750   0.4855   0.01628   0.00777  -0.1112   0.6623   0.0382
  -0.500   0.5146   0.01581   0.00711  -0.1113   0.6546   0.0393
  -0.250   0.5434   0.01507   0.00632  -0.1116   0.6470   0.0406
   0.000   0.5720   0.01463   0.00579  -0.1117   0.6388   0.0409
   0.250   0.6007   0.01424   0.00535  -0.1117   0.6307   0.0411
   0.500   0.6291   0.01391   0.00498  -0.1117   0.6225   0.0414
   0.750   0.6577   0.01362   0.00469  -0.1118   0.6144   0.0421
   1.000   0.6861   0.01340   0.00446  -0.1119   0.6064   0.0429
   1.250   0.7147   0.01322   0.00429  -0.1120   0.5979   0.0440
   1.500   0.7430   0.01311   0.00416  -0.1121   0.5895   0.0454
   1.750   0.7713   0.01306   0.00410  -0.1121   0.5797   0.0483
   2.000   0.7997   0.01299   0.00400  -0.1122   0.5702   0.0508
   2.250   0.8278   0.01296   0.00395  -0.1122   0.5600   0.0533
   2.500   0.8559   0.01297   0.00394  -0.1122   0.5497   0.0572
   2.750   0.8838   0.01299   0.00396  -0.1122   0.5394   0.0677
   3.000   0.9030   0.01139   0.00412  -0.1105   0.5281   1.0000
   3.250   0.9304   0.01157   0.00419  -0.1103   0.5143   1.0000
   3.500   0.9576   0.01177   0.00429  -0.1102   0.4993   1.0000
   3.750   0.9845   0.01198   0.00442  -0.1100   0.4835   1.0000
   4.000   1.0113   0.01222   0.00457  -0.1098   0.4678   1.0000
   4.250   1.0379   0.01247   0.00476  -0.1097   0.4525   1.0000
   4.500   1.0643   0.01275   0.00497  -0.1094   0.4368   1.0000
   4.750   1.0904   0.01305   0.00520  -0.1092   0.4216   1.0000
   5.000   1.1166   0.01334   0.00546  -0.1090   0.4088   1.0000
   5.250   1.1428   0.01364   0.00576  -0.1088   0.3981   1.0000
   5.500   1.1686   0.01398   0.00607  -0.1085   0.3867   1.0000
   5.750   1.1939   0.01434   0.00639  -0.1082   0.3749   1.0000
   6.000   1.2194   0.01468   0.00675  -0.1079   0.3635   1.0000
   6.250   1.2447   0.01504   0.00712  -0.1076   0.3529   1.0000
   6.500   1.2695   0.01544   0.00751  -0.1072   0.3428   1.0000
   6.750   1.2941   0.01583   0.00792  -0.1068   0.3311   1.0000
   7.000   1.3183   0.01623   0.00837  -0.1064   0.3176   1.0000
   7.250   1.3422   0.01666   0.00882  -0.1059   0.3035   1.0000
   7.500   1.3659   0.01709   0.00929  -0.1054   0.2887   1.0000
   7.750   1.3882   0.01762   0.00982  -0.1047   0.2661   1.0000
   8.000   1.4072   0.01841   0.01043  -0.1037   0.2157   1.0000
   8.250   1.4188   0.01995   0.01153  -0.1019   0.1576   1.0000
   8.500   1.4345   0.02105   0.01254  -0.1005   0.1378   1.0000
   8.750   1.4506   0.02204   0.01350  -0.0991   0.1248   1.0000
   9.000   1.4667   0.02296   0.01445  -0.0977   0.1143   1.0000
   9.250   1.4833   0.02378   0.01533  -0.0963   0.1059   1.0000
   9.500   1.4971   0.02475   0.01632  -0.0946   0.0966   1.0000
   9.750   1.5115   0.02561   0.01723  -0.0930   0.0865   1.0000
  10.000   1.5232   0.02651   0.01819  -0.0910   0.0762   1.0000
  10.250   1.5312   0.02764   0.01933  -0.0886   0.0644   1.0000
  10.500   1.5354   0.02914   0.02077  -0.0861   0.0508   1.0000
  10.750   1.5371   0.03096   0.02255  -0.0837   0.0376   1.0000
  11.000   1.5374   0.03305   0.02462  -0.0815   0.0291   1.0000
  11.250   1.5386   0.03520   0.02682  -0.0797   0.0249   1.0000
  11.500   1.5397   0.03748   0.02917  -0.0781   0.0225   1.0000
  11.750   1.5405   0.03991   0.03170  -0.0768   0.0210   1.0000
  12.000   1.5421   0.04235   0.03431  -0.0757   0.0199   1.0000
  12.250   1.5422   0.04503   0.03713  -0.0748   0.0189   1.0000
  12.500   1.5408   0.04798   0.04021  -0.0740   0.0180   1.0000
  12.750   1.5368   0.05130   0.04365  -0.0735   0.0172   1.0000
  13.000   1.5300   0.05508   0.04755  -0.0731   0.0166   1.0000
  13.250   1.5276   0.05838   0.05102  -0.0728   0.0161   1.0000
  13.500   1.5236   0.06196   0.05475  -0.0727   0.0156   1.0000
  13.750   1.5182   0.06578   0.05872  -0.0728   0.0152   1.0000
  14.000   1.5122   0.06980   0.06289  -0.0730   0.0149   1.0000
  14.250   1.5056   0.07403   0.06726  -0.0734   0.0146   1.0000
  14.500   1.4987   0.07841   0.07178  -0.0740   0.0143   1.0000
  14.750   1.4917   0.08292   0.07644  -0.0748   0.0140   1.0000
  15.000   1.4843   0.08756   0.08121  -0.0757   0.0137   1.0000
  15.250   1.4768   0.09231   0.08608  -0.0767   0.0135   1.0000
  15.500   1.4695   0.09710   0.09099  -0.0779   0.0133   1.0000
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