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GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 242 (MVA PR.2) AIRFOIL (goe242-il)
Reynolds number: 1,000,000
Max Cl/Cd: 146.36 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe242-il-1000000.txt
Download as CSV file: xf-goe242-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 242 (MVA PR.2) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.0664   0.09486   0.09242  -0.0831   0.7843   0.0173
 -10.000  -0.0575   0.09223   0.08974  -0.0846   0.7745   0.0175
  -9.750  -0.2511   0.02844   0.02502  -0.1524   0.7788   0.0163
  -9.500  -0.2054   0.02327   0.01943  -0.1676   0.7692   0.0170
  -9.250  -0.1696   0.02247   0.01853  -0.1717   0.7580   0.0173
  -9.000  -0.1355   0.02185   0.01781  -0.1748   0.7444   0.0176
  -8.750  -0.1028   0.02126   0.01710  -0.1773   0.7279   0.0179
  -8.500  -0.0698   0.02046   0.01611  -0.1800   0.7073   0.0185
  -8.250  -0.0353   0.01931   0.01465  -0.1831   0.6841   0.0195
  -7.500   0.0638   0.01661   0.01135  -0.1898   0.6361   0.0214
  -7.250   0.0952   0.01627   0.01093  -0.1911   0.6262   0.0220
  -7.000   0.1273   0.01579   0.01033  -0.1924   0.6174   0.0227
  -6.750   0.1597   0.01535   0.00976  -0.1937   0.6104   0.0236
  -6.500   0.1922   0.01520   0.00946  -0.1950   0.6038   0.0243
  -6.250   0.2245   0.01407   0.00822  -0.1965   0.5977   0.0252
  -6.000   0.2564   0.01356   0.00769  -0.1977   0.5932   0.0259
  -5.750   0.2881   0.01321   0.00732  -0.1987   0.5883   0.0265
  -5.500   0.3197   0.01295   0.00699  -0.1997   0.5835   0.0274
  -5.250   0.3516   0.01266   0.00665  -0.2007   0.5794   0.0283
  -5.000   0.3837   0.01234   0.00630  -0.2017   0.5757   0.0289
  -4.750   0.4155   0.01214   0.00603  -0.2026   0.5719   0.0294
  -4.500   0.4483   0.01176   0.00560  -0.2038   0.5683   0.0300
  -4.250   0.4832   0.01124   0.00504  -0.2058   0.5646   0.0311
  -4.000   0.5165   0.01095   0.00474  -0.2071   0.5622   0.0319
  -3.750   0.5495   0.01071   0.00447  -0.2084   0.5595   0.0326
  -3.500   0.5821   0.01051   0.00423  -0.2095   0.5567   0.0334
  -3.250   0.6144   0.01035   0.00402  -0.2106   0.5540   0.0342
  -3.000   0.6460   0.01026   0.00387  -0.2114   0.5512   0.0351
  -2.750   0.6770   0.01022   0.00378  -0.2122   0.5482   0.0357
  -2.500   0.7099   0.01000   0.00351  -0.2133   0.5464   0.0370
  -2.250   0.7417   0.00987   0.00336  -0.2142   0.5442   0.0385
  -2.000   0.7729   0.00979   0.00326  -0.2150   0.5420   0.0403
  -1.750   0.8037   0.00975   0.00319  -0.2156   0.5394   0.0423
  -1.500   0.8342   0.00973   0.00313  -0.2162   0.5356   0.0488
  -1.250   0.8742   0.00881   0.00289  -0.2199   0.5309   0.3399
  -1.000   0.9047   0.00875   0.00296  -0.2204   0.5275   0.3966
  -0.750   0.9341   0.00880   0.00302  -0.2207   0.5245   0.4135
  -0.500   0.9633   0.00889   0.00307  -0.2210   0.5218   0.4227
  -0.250   0.9922   0.00900   0.00316  -0.2212   0.5188   0.4305
   0.000   1.0208   0.00916   0.00326  -0.2213   0.5156   0.4375
   0.250   1.0503   0.00918   0.00332  -0.2216   0.5134   0.4432
   0.500   1.0795   0.00923   0.00338  -0.2219   0.5107   0.4469
   0.750   1.1085   0.00931   0.00344  -0.2221   0.5081   0.4511
   1.000   1.1373   0.00940   0.00352  -0.2223   0.5056   0.4563
   1.250   1.1660   0.00950   0.00361  -0.2225   0.5031   0.4595
   1.500   1.1943   0.00963   0.00372  -0.2227   0.5002   0.4621
   1.750   1.2233   0.00969   0.00380  -0.2229   0.4983   0.4643
   2.000   1.2523   0.00973   0.00386  -0.2232   0.4960   0.4666
   2.250   1.2811   0.00979   0.00393  -0.2234   0.4932   0.4687
   2.500   1.3096   0.00988   0.00401  -0.2236   0.4901   0.4707
   2.750   1.3378   0.00996   0.00409  -0.2238   0.4870   0.4740
   3.000   1.3655   0.01011   0.00423  -0.2239   0.4836   0.4769
   3.250   1.3942   0.01015   0.00432  -0.2241   0.4813   0.4796
   3.500   1.4227   0.01021   0.00441  -0.2244   0.4783   0.4820
   3.750   1.4508   0.01030   0.00451  -0.2245   0.4747   0.4845
   4.000   1.4782   0.01044   0.00463  -0.2245   0.4708   0.4869
   4.250   1.5057   0.01055   0.00475  -0.2246   0.4669   0.4899
   4.500   1.5339   0.01059   0.00485  -0.2248   0.4616   0.4924
   4.750   1.5609   0.01073   0.00498  -0.2248   0.4549   0.4948
   5.000   1.5880   0.01085   0.00512  -0.2248   0.4480   0.4972
   5.250   1.6139   0.01105   0.00527  -0.2246   0.4349   0.4998
   5.500   1.6384   0.01134   0.00547  -0.2242   0.4126   0.5023
   5.750   1.6594   0.01189   0.00583  -0.2233   0.3804   0.5043
   6.000   1.6777   0.01261   0.00637  -0.2219   0.3470   0.5073
   6.250   1.6970   0.01324   0.00688  -0.2206   0.3236   0.5098
   6.500   1.7161   0.01383   0.00738  -0.2194   0.3052   0.5123
   6.750   1.7352   0.01439   0.00787  -0.2181   0.2897   0.5149
   7.000   1.7542   0.01491   0.00833  -0.2168   0.2768   0.5175
   7.250   1.7723   0.01543   0.00880  -0.2153   0.2657   0.5198
   7.500   1.7882   0.01600   0.00932  -0.2135   0.2536   0.5225
   7.750   1.8026   0.01653   0.00984  -0.2113   0.2425   0.5256
   8.000   1.8130   0.01711   0.01041  -0.2084   0.2333   0.5285
   8.250   1.8241   0.01786   0.01111  -0.2059   0.2231   0.5314
   8.500   1.8370   0.01855   0.01179  -0.2038   0.2135   0.5343
   8.750   1.8472   0.01944   0.01264  -0.2013   0.2022   0.5367
   9.000   1.8539   0.02058   0.01372  -0.1986   0.1874   0.5398
   9.250   1.8501   0.02245   0.01545  -0.1947   0.1615   0.5423
   9.500   1.8243   0.02607   0.01878  -0.1886   0.1151   0.5439
   9.750   1.7994   0.03006   0.02262  -0.1834   0.0767   0.5456
  10.000   1.7918   0.03291   0.02544  -0.1804   0.0606   0.5479
  10.250   1.7892   0.03544   0.02795  -0.1781   0.0489   0.5505
  10.500   1.7767   0.03897   0.03139  -0.1752   0.0274   0.5525
  10.750   1.7677   0.04237   0.03478  -0.1728   0.0160   0.5548
  11.000   1.7704   0.04473   0.03723  -0.1714   0.0149   0.5582
  11.250   1.7713   0.04733   0.03992  -0.1700   0.0139   0.5615
  11.500   1.7717   0.05009   0.04277  -0.1687   0.0130   0.5648
  11.750   1.7742   0.05269   0.04544  -0.1677   0.0126   0.5681
  12.000   1.7760   0.05541   0.04825  -0.1667   0.0122   0.5713
  12.250   1.7765   0.05832   0.05126  -0.1657   0.0117   0.5749
  12.500   1.7760   0.06140   0.05442  -0.1648   0.0114   0.5785
  12.750   1.7735   0.06476   0.05787  -0.1639   0.0110   0.5821
  13.000   1.7691   0.06838   0.06158  -0.1631   0.0106   0.5853
  13.250   1.7612   0.07249   0.06582  -0.1622   0.0102   0.5887
  13.500   1.7611   0.07563   0.06905  -0.1616   0.0101   0.5931
  13.750   1.7594   0.07901   0.07252  -0.1610   0.0099   0.5978
  14.000   1.7567   0.08255   0.07615  -0.1605   0.0097   0.6023
  14.250   1.7541   0.08610   0.07979  -0.1601   0.0095   0.6072
  14.500   1.7500   0.08986   0.08364  -0.1597   0.0093   0.6124
  14.750   1.7451   0.09376   0.08764  -0.1594   0.0091   0.6174
  15.000   1.7409   0.09761   0.09159  -0.1592   0.0089   0.6231
  15.250   1.7353   0.10172   0.09580  -0.1591   0.0087   0.6292
  15.500   1.7289   0.10597   0.10015  -0.1591   0.0086   0.6355
  15.750   1.7220   0.11028   0.10456  -0.1592   0.0084   0.6427
  16.000   1.7112   0.11527   0.10967  -0.1596   0.0082   0.6497
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