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GOE 243 (MVA PR.3) AIRFOIL (goe243-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 243 (MVA PR.3) AIRFOIL (goe243-il)
Reynolds number: 500,000
Max Cl/Cd: 99.11 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe243-il-500000.txt
Download as CSV file: xf-goe243-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 243 (MVA PR.3) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500   0.1459   0.08951   0.08622  -0.1122   0.8017   0.0427
  -9.250   0.1567   0.08721   0.08391  -0.1134   0.7947   0.0433
  -9.000   0.1324   0.07678   0.07347  -0.1232   0.7891   0.0466
  -8.750   0.1474   0.07552   0.07216  -0.1227   0.7824   0.0468
  -8.500   0.1619   0.07407   0.07069  -0.1229   0.7766   0.0471
  -8.250   0.1758   0.07243   0.06905  -0.1235   0.7708   0.0474
  -8.000   0.1884   0.07051   0.06712  -0.1245   0.7650   0.0479
  -7.750   0.1993   0.06823   0.06479  -0.1259   0.7595   0.0486
  -7.500   0.1649   0.02664   0.02161  -0.2031   0.7525   0.0413
  -7.250   0.1944   0.02435   0.01924  -0.2055   0.7472   0.0408
  -7.000   0.2284   0.02236   0.01703  -0.2089   0.7420   0.0404
  -6.750   0.2625   0.02074   0.01518  -0.2116   0.7368   0.0402
  -6.500   0.2958   0.01940   0.01370  -0.2137   0.7317   0.0401
  -6.250   0.3284   0.01834   0.01251  -0.2153   0.7263   0.0402
  -6.000   0.3607   0.01755   0.01156  -0.2166   0.7210   0.0405
  -5.750   0.3934   0.01696   0.01083  -0.2179   0.7157   0.0410
  -5.500   0.4259   0.01644   0.01022  -0.2190   0.7102   0.0414
  -5.250   0.4553   0.01567   0.00944  -0.2194   0.7048   0.0418
  -5.000   0.4854   0.01516   0.00890  -0.2199   0.6994   0.0422
  -4.750   0.5166   0.01478   0.00852  -0.2207   0.6939   0.0428
  -4.500   0.5483   0.01442   0.00817  -0.2215   0.6879   0.0434
  -4.250   0.5803   0.01411   0.00782  -0.2225   0.6822   0.0442
  -4.000   0.6128   0.01386   0.00749  -0.2235   0.6764   0.0449
  -3.750   0.6455   0.01355   0.00718  -0.2246   0.6705   0.0458
  -3.500   0.6784   0.01328   0.00686  -0.2257   0.6639   0.0466
  -3.250   0.7128   0.01294   0.00646  -0.2274   0.6574   0.0480
  -3.000   0.7456   0.01270   0.00623  -0.2286   0.6507   0.0498
  -2.750   0.7776   0.01253   0.00600  -0.2295   0.6428   0.0517
  -2.500   0.8111   0.01227   0.00568  -0.2309   0.6347   0.0541
  -2.250   0.8429   0.01210   0.00548  -0.2317   0.6261   0.0572
  -2.000   0.8747   0.01196   0.00526  -0.2326   0.6180   0.0619
  -1.500   0.9462   0.01093   0.00463  -0.2370   0.6021   0.2462
  -1.250   0.9757   0.01095   0.00471  -0.2373   0.5941   0.3039
  -1.000   1.0041   0.01105   0.00477  -0.2373   0.5846   0.3210
  -0.750   1.0318   0.01118   0.00487  -0.2371   0.5751   0.3329
  -0.500   1.0595   0.01132   0.00494  -0.2370   0.5646   0.3417
  -0.250   1.0865   0.01146   0.00505  -0.2368   0.5546   0.3513
   0.000   1.1135   0.01164   0.00517  -0.2365   0.5436   0.3600
   0.250   1.1399   0.01182   0.00530  -0.2362   0.5331   0.3697
   0.500   1.1659   0.01203   0.00547  -0.2357   0.5222   0.3785
   0.750   1.1920   0.01224   0.00560  -0.2353   0.5120   0.3846
   1.000   1.2173   0.01244   0.00574  -0.2348   0.5011   0.3910
   1.250   1.2431   0.01262   0.00591  -0.2344   0.4912   0.3968
   1.500   1.2674   0.01289   0.00608  -0.2338   0.4812   0.4015
   1.750   1.2930   0.01308   0.00624  -0.2333   0.4727   0.4061
   2.000   1.3172   0.01332   0.00642  -0.2327   0.4641   0.4114
   2.250   1.3415   0.01355   0.00664  -0.2321   0.4567   0.4176
   2.500   1.3658   0.01378   0.00685  -0.2314   0.4492   0.4239
   3.000   1.4120   0.01431   0.00733  -0.2298   0.4349   0.4366
   3.250   1.4340   0.01460   0.00760  -0.2287   0.4278   0.4436
   3.500   1.4534   0.01496   0.00790  -0.2273   0.4214   0.4506
   3.750   1.4746   0.01517   0.00815  -0.2261   0.4163   0.4579
   4.000   1.4939   0.01547   0.00847  -0.2246   0.4106   0.4655
   4.250   1.5125   0.01590   0.00884  -0.2230   0.4049   0.4735
   4.500   1.5337   0.01622   0.00921  -0.2220   0.4000   0.4815
   4.750   1.5547   0.01656   0.00957  -0.2209   0.3946   0.4901
   5.000   1.5733   0.01702   0.00999  -0.2195   0.3884   0.4982
   5.250   1.5909   0.01752   0.01050  -0.2179   0.3826   0.5054
   5.500   1.6120   0.01787   0.01090  -0.2169   0.3780   0.5134
   5.750   1.6310   0.01833   0.01134  -0.2156   0.3727   0.5207
   6.000   1.6471   0.01892   0.01194  -0.2139   0.3672   0.5268
   6.250   1.6659   0.01941   0.01245  -0.2126   0.3625   0.5338
   6.500   1.6849   0.01990   0.01294  -0.2115   0.3574   0.5409
   6.750   1.7014   0.02050   0.01357  -0.2099   0.3519   0.5466
   7.000   1.7156   0.02125   0.01431  -0.2081   0.3464   0.5525
   7.250   1.7344   0.02177   0.01488  -0.2070   0.3413   0.5590
   7.500   1.7503   0.02246   0.01557  -0.2056   0.3350   0.5642
   7.750   1.7620   0.02340   0.01650  -0.2036   0.3286   0.5686
   8.000   1.7792   0.02405   0.01719  -0.2024   0.3222   0.5739
   8.250   1.7910   0.02505   0.01818  -0.2006   0.3143   0.5793
   8.500   1.8040   0.02601   0.01914  -0.1990   0.3062   0.5841
   8.750   1.8129   0.02725   0.02037  -0.1970   0.2962   0.5883
   9.000   1.8229   0.02846   0.02158  -0.1952   0.2851   0.5929
   9.250   1.8280   0.03008   0.02315  -0.1930   0.2718   0.5974
   9.500   1.8298   0.03201   0.02500  -0.1906   0.2557   0.6011
   9.750   1.8287   0.03422   0.02714  -0.1881   0.2379   0.6043
  10.000   1.8262   0.03664   0.02949  -0.1856   0.2218   0.6076
  10.250   1.8248   0.03905   0.03186  -0.1833   0.2105   0.6113
  10.500   1.8250   0.04140   0.03419  -0.1813   0.2026   0.6151
  10.750   1.8277   0.04360   0.03638  -0.1796   0.1974   0.6189
  11.000   1.8322   0.04566   0.03848  -0.1781   0.1938   0.6224
  11.250   1.8351   0.04791   0.04077  -0.1766   0.1908   0.6257
  11.500   1.8367   0.05030   0.04319  -0.1750   0.1881   0.6293
  11.750   1.8373   0.05288   0.04580  -0.1735   0.1857   0.6328
  12.000   1.8442   0.05482   0.04780  -0.1724   0.1844   0.6368
  12.250   1.8501   0.05693   0.04999  -0.1714   0.1833   0.6403
  12.500   1.8557   0.05903   0.05217  -0.1703   0.1821   0.6436
  12.750   1.8600   0.06132   0.05452  -0.1693   0.1810   0.6469
  13.000   1.8643   0.06361   0.05688  -0.1683   0.1800   0.6505
  13.250   1.8679   0.06599   0.05932  -0.1673   0.1790   0.6541
  13.500   1.8713   0.06844   0.06182  -0.1663   0.1780   0.6573
  13.750   1.8748   0.07086   0.06430  -0.1655   0.1770   0.6605
  14.000   1.8769   0.07345   0.06695  -0.1646   0.1760   0.6636
  14.250   1.8800   0.07588   0.06943  -0.1637   0.1749   0.6672
  14.500   1.8830   0.07834   0.07194  -0.1629   0.1740   0.6707
  14.750   1.8876   0.08058   0.07422  -0.1621   0.1731   0.6743
  15.000   1.8942   0.08253   0.07621  -0.1613   0.1722   0.6778
  15.250   1.9021   0.08428   0.07801  -0.1605   0.1715   0.6815
  15.500   1.9089   0.08631   0.08012  -0.1600   0.1712   0.6856
  15.750   1.9160   0.08830   0.08219  -0.1594   0.1708   0.6897
  16.000   1.9237   0.09020   0.08416  -0.1589   0.1705   0.6937
  16.250   1.9314   0.09210   0.08615  -0.1585   0.1701   0.6975
  16.500   1.9373   0.09427   0.08840  -0.1581   0.1695   0.7015
  16.750   1.9431   0.09646   0.09067  -0.1578   0.1687   0.7061
  17.000   1.9491   0.09860   0.09289  -0.1575   0.1678   0.7109
  17.250   1.9547   0.10080   0.09517  -0.1572   0.1669   0.7156
  17.500   1.9599   0.10303   0.09748  -0.1570   0.1659   0.7207
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