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GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 242 (MVA PR.2) AIRFOIL (goe242-il)
Reynolds number: 500,000
Max Cl/Cd: 114.64 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe242-il-500000-n5.txt
Download as CSV file: xf-goe242-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.0846   0.09083   0.08757  -0.0868   0.7534   0.0121
 -10.250  -0.0783   0.08760   0.08430  -0.0887   0.7420   0.0123
 -10.000  -0.2075   0.05093   0.04762  -0.1147   0.7488   0.0137
  -9.750  -0.2434   0.02755   0.02313  -0.1549   0.7382   0.0150
  -9.500  -0.2103   0.02662   0.02210  -0.1590   0.7236   0.0153
  -9.250  -0.1761   0.02573   0.02107  -0.1632   0.7066   0.0156
  -9.000  -0.1406   0.02465   0.01981  -0.1679   0.6884   0.0160
  -8.750  -0.1034   0.02311   0.01798  -0.1733   0.6713   0.0167
  -8.500  -0.0656   0.02074   0.01514  -0.1788   0.6570   0.0181
  -8.250  -0.0316   0.01979   0.01397  -0.1818   0.6450   0.0187
  -8.000   0.0010   0.01945   0.01352  -0.1838   0.6345   0.0191
  -7.750   0.0338   0.01908   0.01304  -0.1857   0.6252   0.0197
  -7.500   0.0665   0.01855   0.01236  -0.1876   0.6173   0.0205
  -7.250   0.0996   0.01785   0.01148  -0.1895   0.6101   0.0214
  -7.000   0.1326   0.01729   0.01069  -0.1912   0.6037   0.0223
  -6.750   0.1649   0.01666   0.00999  -0.1927   0.5986   0.0231
  -6.500   0.1969   0.01627   0.00954  -0.1941   0.5935   0.0237
  -6.250   0.2288   0.01589   0.00909  -0.1953   0.5887   0.0244
  -6.000   0.2608   0.01550   0.00861  -0.1966   0.5846   0.0252
  -5.750   0.2931   0.01515   0.00819  -0.1978   0.5807   0.0261
  -5.500   0.3251   0.01484   0.00779  -0.1989   0.5767   0.0269
  -5.250   0.3570   0.01458   0.00744  -0.2000   0.5730   0.0274
  -5.000   0.3902   0.01408   0.00688  -0.2015   0.5696   0.0281
  -4.750   0.4236   0.01369   0.00648  -0.2030   0.5666   0.0291
  -4.500   0.4566   0.01340   0.00617  -0.2044   0.5634   0.0299
  -4.250   0.4896   0.01314   0.00586  -0.2058   0.5600   0.0306
  -4.000   0.5225   0.01291   0.00557  -0.2071   0.5568   0.0312
  -3.750   0.5551   0.01272   0.00530  -0.2083   0.5539   0.0319
  -3.500   0.5875   0.01256   0.00508  -0.2095   0.5514   0.0326
  -3.250   0.6197   0.01240   0.00489  -0.2105   0.5492   0.0334
  -3.000   0.6523   0.01222   0.00467  -0.2117   0.5468   0.0342
  -2.750   0.6848   0.01205   0.00444  -0.2129   0.5444   0.0352
  -2.500   0.7165   0.01195   0.00429  -0.2138   0.5421   0.0363
  -2.250   0.7475   0.01189   0.00418  -0.2146   0.5399   0.0375
  -2.000   0.7782   0.01186   0.00410  -0.2153   0.5378   0.0390
  -1.750   0.8086   0.01187   0.00405  -0.2159   0.5357   0.0409
  -1.500   0.8394   0.01182   0.00400  -0.2166   0.5337   0.0470
  -1.250   0.8764   0.01126   0.00384  -0.2192   0.5316   0.2118
  -1.000   0.9106   0.01089   0.00382  -0.2211   0.5294   0.3532
  -0.750   0.9400   0.01095   0.00392  -0.2215   0.5265   0.3895
  -0.500   0.9687   0.01105   0.00399  -0.2217   0.5222   0.4041
  -0.250   0.9972   0.01118   0.00408  -0.2218   0.5174   0.4151
   0.000   1.0261   0.01125   0.00415  -0.2221   0.5129   0.4251
   0.250   1.0546   0.01135   0.00425  -0.2222   0.5090   0.4342
   0.500   1.0831   0.01147   0.00430  -0.2224   0.5056   0.4383
   0.750   1.1112   0.01160   0.00443  -0.2225   0.5027   0.4438
   1.000   1.1397   0.01171   0.00454  -0.2226   0.5002   0.4503
   1.250   1.1684   0.01179   0.00462  -0.2228   0.4969   0.4538
   1.500   1.1967   0.01188   0.00471  -0.2230   0.4932   0.4564
   1.750   1.2247   0.01199   0.00482  -0.2231   0.4899   0.4590
   2.000   1.2524   0.01213   0.00494  -0.2232   0.4867   0.4617
   2.250   1.2805   0.01222   0.00505  -0.2233   0.4839   0.4640
   2.500   1.3086   0.01232   0.00517  -0.2235   0.4809   0.4668
   2.750   1.3365   0.01243   0.00529  -0.2236   0.4776   0.4696
   3.000   1.3640   0.01256   0.00541  -0.2237   0.4741   0.4722
   3.250   1.3909   0.01270   0.00557  -0.2236   0.4707   0.4748
   3.500   1.4185   0.01281   0.00573  -0.2237   0.4672   0.4776
   3.750   1.4458   0.01293   0.00588  -0.2238   0.4629   0.4802
   4.000   1.4724   0.01308   0.00604  -0.2237   0.4579   0.4825
   4.250   1.4986   0.01325   0.00621  -0.2235   0.4527   0.4850
   4.500   1.5252   0.01338   0.00638  -0.2235   0.4462   0.4876
   4.750   1.5503   0.01359   0.00657  -0.2231   0.4390   0.4898
   5.000   1.5763   0.01375   0.00678  -0.2230   0.4310   0.4920
   5.250   1.6004   0.01399   0.00702  -0.2225   0.4201   0.4943
   5.500   1.6225   0.01434   0.00731  -0.2217   0.4012   0.4966
   5.750   1.6396   0.01497   0.00779  -0.2200   0.3716   0.4990
   6.000   1.6536   0.01577   0.00842  -0.2179   0.3436   0.5013
   6.250   1.6673   0.01656   0.00908  -0.2158   0.3218   0.5036
   6.500   1.6799   0.01733   0.00976  -0.2134   0.3044   0.5057
   6.750   1.6886   0.01805   0.01045  -0.2103   0.2900   0.5079
   7.000   1.6990   0.01881   0.01118  -0.2076   0.2776   0.5104
   7.250   1.7104   0.01962   0.01197  -0.2053   0.2667   0.5131
   7.500   1.7217   0.02048   0.01281  -0.2030   0.2553   0.5158
   7.750   1.7332   0.02137   0.01368  -0.2009   0.2451   0.5185
   8.000   1.7430   0.02239   0.01469  -0.1987   0.2358   0.5209
   8.250   1.7531   0.02344   0.01574  -0.1966   0.2257   0.5233
   8.500   1.7623   0.02461   0.01692  -0.1946   0.2165   0.5256
   8.750   1.7687   0.02602   0.01831  -0.1923   0.2066   0.5281
   9.000   1.7766   0.02738   0.01968  -0.1903   0.1962   0.5309
   9.250   1.7794   0.02920   0.02147  -0.1880   0.1821   0.5338
   9.500   1.7761   0.03159   0.02377  -0.1852   0.1631   0.5364
   9.750   1.7512   0.03598   0.02792  -0.1809   0.1199   0.5380
  10.000   1.7249   0.04080   0.03261  -0.1770   0.0831   0.5393
  10.250   1.7145   0.04436   0.03618  -0.1747   0.0684   0.5413
  10.500   1.7115   0.04733   0.03919  -0.1730   0.0592   0.5437
  10.750   1.7100   0.05026   0.04217  -0.1716   0.0512   0.5463
  11.000   1.7060   0.05354   0.04547  -0.1702   0.0414   0.5489
  11.250   1.6899   0.05831   0.05017  -0.1685   0.0188   0.5508
  11.500   1.6856   0.06185   0.05378  -0.1674   0.0153   0.5533
  11.750   1.6855   0.06494   0.05697  -0.1666   0.0140   0.5558
  12.000   1.6844   0.06818   0.06031  -0.1658   0.0130   0.5585
  12.250   1.6838   0.07136   0.06359  -0.1650   0.0122   0.5616
  12.500   1.6847   0.07440   0.06673  -0.1644   0.0116   0.5651
  12.750   1.6846   0.07759   0.07003  -0.1638   0.0111   0.5687
  13.000   1.6841   0.08084   0.07338  -0.1633   0.0107   0.5720
  13.250   1.6819   0.08433   0.07699  -0.1628   0.0102   0.5754
  13.500   1.6787   0.08800   0.08076  -0.1623   0.0098   0.5789
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