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GOE 133 (MVA H.11) AIRFOIL (goe133-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 133 (MVA H.11) AIRFOIL (goe133-il)
Reynolds number: 500,000
Max Cl/Cd: 92.96 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe133-il-500000-n5.txt
Download as CSV file: xf-goe133-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 133 (MVA H.11) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3517   0.09121   0.08900  -0.0230   1.0000   0.0088
  -8.000  -0.3497   0.08783   0.08566  -0.0243   1.0000   0.0086
  -7.750  -0.3529   0.08480   0.08267  -0.0246   1.0000   0.0083
  -7.500  -0.3433   0.07980   0.07768  -0.0300   0.9940   0.0080
  -6.500  -0.2529   0.01824   0.01402  -0.0906   0.9526   0.0091
  -6.250  -0.2269   0.01610   0.01144  -0.0908   0.9451   0.0097
  -6.000  -0.1997   0.01477   0.00981  -0.0909   0.9383   0.0101
  -5.750  -0.1732   0.01349   0.00828  -0.0908   0.9308   0.0107
  -5.500  -0.1461   0.01278   0.00743  -0.0906   0.9231   0.0113
  -5.250  -0.1191   0.01217   0.00668  -0.0904   0.9146   0.0120
  -5.000  -0.0921   0.01160   0.00595  -0.0901   0.9054   0.0130
  -4.750  -0.0651   0.01113   0.00534  -0.0897   0.8943   0.0139
  -4.500  -0.0380   0.01066   0.00480  -0.0894   0.8825   0.0159
  -4.250  -0.0109   0.01033   0.00437  -0.0891   0.8700   0.0177
  -4.000   0.0163   0.00999   0.00393  -0.0887   0.8555   0.0199
  -3.750   0.0435   0.00985   0.00373  -0.0883   0.8385   0.0232
  -3.500   0.0705   0.00973   0.00350  -0.0879   0.8192   0.0265
  -3.250   0.0978   0.00974   0.00343  -0.0876   0.7982   0.0298
  -3.000   0.1250   0.00972   0.00326  -0.0872   0.7777   0.0324
  -2.750   0.1521   0.00964   0.00310  -0.0870   0.7577   0.0352
  -2.500   0.1795   0.00964   0.00300  -0.0867   0.7372   0.0377
  -2.250   0.2068   0.00964   0.00287  -0.0864   0.7166   0.0402
  -2.000   0.2340   0.00968   0.00277  -0.0861   0.6937   0.0417
  -1.750   0.2608   0.00944   0.00241  -0.0859   0.6668   0.0445
  -1.500   0.2878   0.00942   0.00225  -0.0856   0.6367   0.0467
  -1.250   0.3148   0.00941   0.00210  -0.0853   0.6054   0.0484
  -1.000   0.3418   0.00943   0.00196  -0.0851   0.5770   0.0503
  -0.750   0.3690   0.00946   0.00185  -0.0849   0.5522   0.0521
  -0.500   0.3963   0.00950   0.00178  -0.0848   0.5333   0.0535
  -0.250   0.4239   0.00949   0.00168  -0.0846   0.5172   0.0571
   0.000   0.4514   0.00950   0.00163  -0.0845   0.5023   0.0618
   0.500   0.5067   0.00954   0.00160  -0.0844   0.4762   0.0754
   0.750   0.5344   0.00953   0.00162  -0.0843   0.4646   0.1042
   1.000   0.5620   0.00950   0.00166  -0.0843   0.4531   0.1518
   1.250   0.5818   0.00784   0.00187  -0.0833   0.4443   0.8450
   2.000   0.6678   0.00794   0.00197  -0.0834   0.4193   1.0000
   2.250   0.6953   0.00808   0.00203  -0.0833   0.4107   1.0000
   2.500   0.7229   0.00820   0.00211  -0.0832   0.4014   1.0000
   2.750   0.7504   0.00834   0.00220  -0.0831   0.3919   1.0000
   3.000   0.7776   0.00850   0.00230  -0.0830   0.3798   1.0000
   3.250   0.8047   0.00869   0.00241  -0.0828   0.3618   1.0000
   3.500   0.8311   0.00894   0.00253  -0.0827   0.3376   1.0000
   3.750   0.8571   0.00925   0.00269  -0.0824   0.3045   1.0000
   4.000   0.8825   0.00965   0.00291  -0.0821   0.2688   1.0000
   4.250   0.9081   0.01002   0.00315  -0.0818   0.2445   1.0000
   4.500   0.9339   0.01036   0.00339  -0.0816   0.2267   1.0000
   4.750   0.9599   0.01066   0.00364  -0.0813   0.2135   1.0000
   5.000   0.9859   0.01095   0.00388  -0.0811   0.2034   1.0000
   5.500   1.0380   0.01149   0.00438  -0.0806   0.1864   1.0000
   5.750   1.0638   0.01178   0.00464  -0.0804   0.1797   1.0000
   6.000   1.0900   0.01201   0.00490  -0.0801   0.1749   1.0000
   6.250   1.1159   0.01226   0.00516  -0.0799   0.1694   1.0000
   6.500   1.1413   0.01256   0.00547  -0.0796   0.1623   1.0000
   6.750   1.1671   0.01281   0.00575  -0.0793   0.1553   1.0000
   7.000   1.1922   0.01313   0.00606  -0.0790   0.1466   1.0000
   7.250   1.2170   0.01349   0.00639  -0.0786   0.1311   1.0000
   7.500   1.2372   0.01437   0.00701  -0.0778   0.0861   1.0000
   7.750   1.2602   0.01491   0.00754  -0.0771   0.0779   1.0000
   8.000   1.2834   0.01540   0.00805  -0.0766   0.0708   1.0000
   8.250   1.3059   0.01595   0.00860  -0.0759   0.0633   1.0000
   8.500   1.3288   0.01643   0.00913  -0.0753   0.0579   1.0000
   8.750   1.3514   0.01691   0.00963  -0.0746   0.0530   1.0000
   9.000   1.3731   0.01747   0.01020  -0.0739   0.0481   1.0000
   9.250   1.3954   0.01792   0.01071  -0.0732   0.0445   1.0000
   9.500   1.4160   0.01854   0.01131  -0.0723   0.0390   1.0000
   9.750   1.4371   0.01907   0.01189  -0.0715   0.0347   1.0000
  10.000   1.4565   0.01974   0.01257  -0.0705   0.0286   1.0000
  10.500   1.4872   0.02168   0.01444  -0.0674   0.0126   1.0000
  10.750   1.5028   0.02254   0.01538  -0.0658   0.0107   1.0000
  11.000   1.5162   0.02350   0.01642  -0.0640   0.0094   1.0000
  11.250   1.5265   0.02449   0.01750  -0.0617   0.0085   1.0000
  11.500   1.5369   0.02542   0.01854  -0.0594   0.0079   1.0000
  11.750   1.5456   0.02649   0.01973  -0.0572   0.0073   1.0000
  12.000   1.5524   0.02774   0.02107  -0.0549   0.0068   1.0000
  12.250   1.5562   0.02928   0.02272  -0.0525   0.0064   1.0000
  12.500   1.5615   0.03077   0.02433  -0.0506   0.0061   1.0000
  12.750   1.5663   0.03240   0.02607  -0.0489   0.0058   1.0000
  13.000   1.5695   0.03427   0.02807  -0.0474   0.0055   1.0000
  13.250   1.5711   0.03641   0.03035  -0.0461   0.0053   1.0000
  13.500   1.5716   0.03884   0.03290  -0.0452   0.0051   1.0000
  13.750   1.5705   0.04160   0.03579  -0.0446   0.0050   1.0000
  14.000   1.5676   0.04476   0.03908  -0.0444   0.0048   1.0000
  14.250   1.5625   0.04839   0.04287  -0.0446   0.0047   1.0000
  14.500   1.5551   0.05251   0.04713  -0.0452   0.0046   1.0000
  14.750   1.5447   0.05730   0.05206  -0.0463   0.0045   1.0000
  15.000   1.5319   0.06258   0.05750  -0.0477   0.0044   1.0000
  15.250   1.5188   0.06809   0.06314  -0.0494   0.0044   1.0000
  15.500   1.5066   0.07358   0.06878  -0.0512   0.0044   1.0000
  15.750   1.4934   0.07928   0.07462  -0.0531   0.0043   1.0000
  16.000   1.4790   0.08530   0.08078  -0.0552   0.0043   1.0000
  16.250   1.4637   0.09159   0.08721  -0.0575   0.0043   1.0000
  16.500   1.4481   0.09803   0.09379  -0.0599   0.0042   1.0000
  16.750   1.4324   0.10467   0.10056  -0.0625   0.0042   1.0000
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