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GOE 234 (MVA CA5) AIRFOIL (goe234-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 234 (MVA CA5) AIRFOIL (goe234-il)
Reynolds number: 500,000
Max Cl/Cd: 108.38 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe234-il-500000-n5.txt
Download as CSV file: xf-goe234-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 234 (MVA CA5) 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.3627   0.06103   0.05776  -0.1122   0.8715   0.0249
 -11.500  -0.3842   0.05365   0.05011  -0.1190   0.8594   0.0251
 -11.250  -0.3811   0.04903   0.04534  -0.1251   0.8505   0.0254
 -10.750  -0.3468   0.04364   0.03980  -0.1341   0.8378   0.0261
 -10.500  -0.3251   0.04104   0.03711  -0.1393   0.8320   0.0265
 -10.250  -0.3005   0.03833   0.03427  -0.1451   0.8269   0.0269
 -10.000  -0.2722   0.03572   0.03153  -0.1514   0.8223   0.0274
  -9.750  -0.2409   0.03326   0.02894  -0.1579   0.8176   0.0281
  -9.500  -0.2065   0.03090   0.02640  -0.1646   0.8131   0.0288
  -9.250  -0.1708   0.02896   0.02428  -0.1705   0.8090   0.0293
  -9.000  -0.1352   0.02743   0.02263  -0.1753   0.8054   0.0298
  -8.750  -0.1000   0.02625   0.02141  -0.1794   0.8013   0.0304
  -8.500  -0.0635   0.02509   0.02019  -0.1837   0.7970   0.0310
  -8.250  -0.0273   0.02407   0.01908  -0.1876   0.7930   0.0316
  -7.750   0.0447   0.02229   0.01714  -0.1943   0.7854   0.0329
  -7.500   0.0805   0.02152   0.01630  -0.1973   0.7810   0.0335
  -7.250   0.1163   0.02080   0.01547  -0.2003   0.7766   0.0342
  -7.000   0.1512   0.02021   0.01482  -0.2027   0.7726   0.0349
  -6.750   0.1869   0.01959   0.01417  -0.2055   0.7685   0.0357
  -6.500   0.2228   0.01896   0.01351  -0.2082   0.7637   0.0364
  -6.250   0.2585   0.01838   0.01287  -0.2108   0.7586   0.0373
  -6.000   0.2939   0.01785   0.01226  -0.2132   0.7541   0.0382
  -5.750   0.3294   0.01731   0.01167  -0.2156   0.7494   0.0391
  -5.500   0.3646   0.01680   0.01109  -0.2179   0.7438   0.0401
  -5.250   0.4014   0.01618   0.01042  -0.2208   0.7380   0.0415
  -5.000   0.4372   0.01562   0.00981  -0.2233   0.7325   0.0429
  -4.750   0.4727   0.01508   0.00921  -0.2256   0.7264   0.0445
  -4.500   0.5077   0.01458   0.00862  -0.2278   0.7199   0.0461
  -4.250   0.5441   0.01395   0.00791  -0.2304   0.7134   0.0482
  -4.000   0.5793   0.01338   0.00727  -0.2327   0.7056   0.0508
  -3.750   0.6130   0.01295   0.00673  -0.2344   0.6985   0.0537
  -3.500   0.6480   0.01235   0.00606  -0.2365   0.6910   0.0577
  -3.000   0.7137   0.01155   0.00507  -0.2394   0.6754   0.0668
  -2.500   0.7797   0.01067   0.00412  -0.2424   0.6577   0.1303
  -2.250   0.8125   0.01015   0.00367  -0.2440   0.6487   0.2093
  -2.000   0.8419   0.01015   0.00374  -0.2443   0.6398   0.2552
  -1.750   0.8704   0.01028   0.00378  -0.2443   0.6312   0.2678
  -1.500   0.8990   0.01041   0.00390  -0.2442   0.6221   0.2758
  -1.250   0.9273   0.01054   0.00392  -0.2442   0.6133   0.2821
  -1.000   0.9559   0.01065   0.00402  -0.2442   0.6047   0.2862
  -0.750   0.9837   0.01083   0.00413  -0.2440   0.5955   0.2895
  -0.500   1.0118   0.01097   0.00422  -0.2439   0.5842   0.2932
  -0.250   1.0397   0.01112   0.00427  -0.2438   0.5740   0.2974
   0.000   1.0676   0.01127   0.00440  -0.2437   0.5658   0.3009
   0.250   1.0953   0.01146   0.00457  -0.2435   0.5599   0.3036
   0.500   1.1237   0.01155   0.00466  -0.2435   0.5538   0.3053
   0.750   1.1516   0.01166   0.00474  -0.2435   0.5473   0.3069
   1.000   1.1795   0.01177   0.00481  -0.2434   0.5412   0.3083
   1.250   1.2075   0.01186   0.00487  -0.2434   0.5343   0.3097
   1.500   1.2349   0.01199   0.00496  -0.2433   0.5268   0.3113
   1.750   1.2625   0.01211   0.00504  -0.2432   0.5194   0.3131
   2.000   1.2896   0.01226   0.00514  -0.2430   0.5109   0.3148
   2.250   1.3165   0.01240   0.00529  -0.2428   0.5031   0.3164
   2.500   1.3432   0.01256   0.00544  -0.2425   0.4945   0.3176
   2.750   1.3696   0.01274   0.00560  -0.2422   0.4863   0.3189
   3.000   1.3957   0.01293   0.00577  -0.2418   0.4767   0.3202
   3.250   1.4216   0.01312   0.00595  -0.2415   0.4672   0.3214
   3.500   1.4466   0.01336   0.00615  -0.2409   0.4562   0.3228
   3.750   1.4718   0.01358   0.00634  -0.2404   0.4442   0.3242
   4.000   1.4956   0.01388   0.00658  -0.2397   0.4290   0.3257
   4.250   1.5178   0.01426   0.00687  -0.2387   0.4093   0.3271
   4.750   1.5590   0.01519   0.00757  -0.2361   0.3684   0.3296
   5.000   1.5789   0.01566   0.00796  -0.2347   0.3509   0.3308
   5.250   1.5975   0.01618   0.00841  -0.2331   0.3331   0.3320
   5.500   1.6143   0.01675   0.00890  -0.2312   0.3153   0.3331
   5.750   1.6302   0.01732   0.00942  -0.2291   0.3006   0.3344
   6.000   1.6458   0.01785   0.00992  -0.2269   0.2890   0.3358
   6.250   1.6586   0.01833   0.01041  -0.2241   0.2809   0.3372
   6.500   1.6727   0.01889   0.01096  -0.2218   0.2731   0.3386
   6.750   1.6888   0.01944   0.01152  -0.2198   0.2668   0.3401
   7.000   1.7054   0.01998   0.01208  -0.2180   0.2608   0.3416
   7.250   1.7196   0.02068   0.01277  -0.2159   0.2539   0.3430
   7.500   1.7352   0.02132   0.01342  -0.2140   0.2470   0.3443
   7.750   1.7487   0.02210   0.01418  -0.2119   0.2393   0.3455
   8.000   1.7625   0.02287   0.01497  -0.2099   0.2331   0.3467
   8.250   1.7777   0.02358   0.01572  -0.2081   0.2274   0.3480
   8.500   1.7914   0.02440   0.01658  -0.2062   0.2227   0.3492
   8.750   1.8037   0.02533   0.01753  -0.2041   0.2179   0.3506
   9.000   1.8187   0.02610   0.01837  -0.2025   0.2134   0.3521
   9.250   1.8316   0.02704   0.01935  -0.2006   0.2079   0.3538
   9.500   1.8412   0.02825   0.02055  -0.1985   0.2015   0.3553
   9.750   1.8541   0.02922   0.02158  -0.1967   0.1941   0.3569
  10.000   1.8623   0.03060   0.02295  -0.1946   0.1844   0.3583
  10.250   1.8692   0.03212   0.02443  -0.1924   0.1694   0.3595
  10.500   1.8535   0.03557   0.02757  -0.1881   0.1237   0.3602
  10.750   1.8401   0.03899   0.03084  -0.1842   0.0974   0.3608
  11.000   1.8349   0.04179   0.03359  -0.1814   0.0811   0.3616
  11.250   1.8186   0.04577   0.03742  -0.1779   0.0490   0.3622
  11.500   1.8132   0.04888   0.04051  -0.1755   0.0385   0.3631
  11.750   1.8150   0.05133   0.04302  -0.1738   0.0354   0.3641
  12.000   1.8177   0.05372   0.04549  -0.1722   0.0332   0.3652
  12.250   1.8218   0.05603   0.04789  -0.1708   0.0319   0.3665
  12.500   1.8246   0.05853   0.05047  -0.1695   0.0308   0.3679
  12.750   1.8263   0.06120   0.05323  -0.1681   0.0297   0.3694
  13.000   1.8268   0.06406   0.05618  -0.1669   0.0287   0.3708
  13.250   1.8271   0.06699   0.05920  -0.1657   0.0278   0.3722
  13.500   1.8296   0.06973   0.06204  -0.1647   0.0272   0.3736
  13.750   1.8311   0.07260   0.06501  -0.1638   0.0266   0.3748
  14.000   1.8316   0.07565   0.06815  -0.1630   0.0259   0.3759
  14.250   1.8305   0.07896   0.07155  -0.1622   0.0252   0.3769
  14.500   1.8279   0.08248   0.07517  -0.1615   0.0246   0.3779
  14.750   1.8241   0.08620   0.07900  -0.1609   0.0239   0.3790
  15.000   1.8180   0.09032   0.08322  -0.1604   0.0233   0.3799
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