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GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 242 (MVA PR.2) AIRFOIL (goe242-il)
Reynolds number: 500,000
Max Cl/Cd: 116.78 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe242-il-500000.txt
Download as CSV file: xf-goe242-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500   0.0389   0.09029   0.08753  -0.0896   0.8120   0.0263
 -10.250   0.0439   0.08708   0.08429  -0.0906   0.8037   0.0271
 -10.000  -0.0416   0.09542   0.09263  -0.0864   0.8325   0.0257
  -9.750  -0.0334   0.09269   0.08985  -0.0875   0.8241   0.0263
  -9.500  -0.0260   0.08957   0.08671  -0.0892   0.8147   0.0271
  -9.250  -0.0215   0.08557   0.08267  -0.0918   0.8059   0.0284
  -9.000  -0.0369   0.07397   0.07108  -0.1025   0.7982   0.0296
  -8.750  -0.0377   0.06930   0.06639  -0.1044   0.7888   0.0301
  -8.500  -0.0257   0.06810   0.06514  -0.1044   0.7766   0.0304
  -8.250  -0.0142   0.06631   0.06331  -0.1053   0.7631   0.0308
  -8.000  -0.0057   0.06348   0.06043  -0.1073   0.7485   0.0315
  -7.750  -0.0019   0.05930   0.05621  -0.1108   0.7331   0.0324
  -7.500   0.0349   0.03164   0.02730  -0.1746   0.7197   0.0365
  -7.250   0.0579   0.02994   0.02562  -0.1748   0.7025   0.0374
  -7.000   0.0884   0.02819   0.02369  -0.1779   0.6863   0.0388
  -6.750   0.1348   0.02530   0.02010  -0.1866   0.6724   0.0444
  -6.500   0.1786   0.02114   0.01519  -0.1915   0.6617   0.0363
  -6.250   0.2093   0.01985   0.01377  -0.1924   0.6519   0.0352
  -6.000   0.2427   0.01840   0.01208  -0.1942   0.6438   0.0351
  -5.750   0.2765   0.01810   0.01153  -0.1957   0.6362   0.0358
  -5.500   0.3079   0.01615   0.00946  -0.1971   0.6302   0.0367
  -5.250   0.3391   0.01533   0.00861  -0.1980   0.6244   0.0374
  -5.000   0.3705   0.01476   0.00798  -0.1989   0.6191   0.0380
  -4.750   0.4020   0.01433   0.00747  -0.1998   0.6143   0.0387
  -4.500   0.4341   0.01393   0.00706  -0.2009   0.6098   0.0399
  -4.250   0.4664   0.01359   0.00668  -0.2020   0.6053   0.0410
  -4.000   0.4991   0.01329   0.00630  -0.2032   0.6012   0.0416
  -3.750   0.5320   0.01307   0.00599  -0.2044   0.5975   0.0423
  -3.500   0.5651   0.01282   0.00571  -0.2056   0.5943   0.0429
  -3.250   0.6007   0.01239   0.00523  -0.2077   0.5910   0.0447
  -3.000   0.6345   0.01214   0.00493  -0.2092   0.5878   0.0464
  -2.750   0.6671   0.01201   0.00472  -0.2103   0.5848   0.0481
  -2.500   0.6990   0.01198   0.00458  -0.2113   0.5818   0.0501
  -2.250   0.7307   0.01189   0.00445  -0.2121   0.5794   0.0529
  -2.000   0.7630   0.01175   0.00434  -0.2132   0.5766   0.0653
  -1.750   0.8048   0.01074   0.00416  -0.2175   0.5737   0.3786
  -1.500   0.8341   0.01090   0.00433  -0.2177   0.5712   0.4157
  -1.250   0.8631   0.01109   0.00448  -0.2178   0.5689   0.4312
  -1.000   0.8920   0.01134   0.00468  -0.2179   0.5664   0.4432
  -0.750   0.9208   0.01155   0.00484  -0.2180   0.5634   0.4523
  -0.500   0.9494   0.01162   0.00493  -0.2181   0.5593   0.4583
  -0.250   0.9777   0.01173   0.00503  -0.2181   0.5545   0.4645
   0.000   1.0063   0.01193   0.00511  -0.2182   0.5504   0.4707
   0.250   1.0346   0.01208   0.00530  -0.2182   0.5472   0.4761
   0.500   1.0629   0.01220   0.00545  -0.2183   0.5442   0.4818
   0.750   1.0919   0.01227   0.00550  -0.2185   0.5410   0.4850
   1.000   1.1208   0.01236   0.00553  -0.2188   0.5378   0.4876
   1.250   1.1494   0.01242   0.00558  -0.2190   0.5347   0.4902
   1.500   1.1779   0.01259   0.00573  -0.2192   0.5317   0.4925
   1.750   1.2064   0.01264   0.00582  -0.2194   0.5292   0.4951
   2.000   1.2349   0.01271   0.00592  -0.2196   0.5265   0.4977
   2.250   1.2634   0.01279   0.00600  -0.2198   0.5237   0.5006
   2.500   1.2918   0.01290   0.00609  -0.2200   0.5209   0.5037
   2.750   1.3200   0.01301   0.00618  -0.2202   0.5181   0.5065
   3.000   1.3480   0.01317   0.00636  -0.2204   0.5152   0.5092
   3.250   1.3756   0.01322   0.00649  -0.2204   0.5122   0.5120
   3.500   1.4033   0.01329   0.00659  -0.2205   0.5086   0.5148
   3.750   1.4309   0.01337   0.00669  -0.2206   0.5049   0.5173
   4.000   1.4584   0.01352   0.00679  -0.2207   0.5014   0.5198
   4.250   1.4858   0.01362   0.00693  -0.2208   0.4979   0.5221
   4.500   1.5129   0.01367   0.00707  -0.2207   0.4940   0.5244
   4.750   1.5396   0.01375   0.00721  -0.2207   0.4898   0.5270
   5.000   1.5660   0.01390   0.00735  -0.2205   0.4856   0.5300
   5.250   1.5922   0.01401   0.00752  -0.2204   0.4807   0.5332
   5.500   1.6180   0.01409   0.00765  -0.2202   0.4741   0.5361
   5.750   1.6428   0.01425   0.00778  -0.2198   0.4676   0.5387
   6.000   1.6678   0.01431   0.00794  -0.2194   0.4581   0.5414
   6.250   1.6910   0.01448   0.00812  -0.2188   0.4453   0.5442
   6.500   1.7131   0.01471   0.00834  -0.2179   0.4294   0.5474
   6.750   1.7329   0.01507   0.00864  -0.2167   0.4086   0.5505
   7.000   1.7489   0.01565   0.00909  -0.2148   0.3817   0.5535
   7.250   1.7595   0.01648   0.00977  -0.2121   0.3535   0.5564
   8.000   1.7801   0.01916   0.01222  -0.2022   0.3024   0.5654
   8.250   1.7905   0.02004   0.01309  -0.1998   0.2909   0.5686
   8.500   1.7999   0.02101   0.01405  -0.1974   0.2804   0.5716
   8.750   1.8089   0.02205   0.01509  -0.1950   0.2704   0.5747
   9.000   1.8197   0.02304   0.01610  -0.1930   0.2611   0.5781
   9.250   1.8267   0.02432   0.01737  -0.1907   0.2519   0.5818
   9.500   1.8360   0.02551   0.01858  -0.1887   0.2425   0.5856
   9.750   1.8426   0.02693   0.02002  -0.1866   0.2321   0.5892
  10.000   1.8465   0.02863   0.02171  -0.1843   0.2225   0.5930
  10.250   1.8507   0.03037   0.02345  -0.1822   0.2109   0.5970
  10.500   1.8521   0.03241   0.02546  -0.1800   0.1976   0.6009
  10.750   1.8480   0.03501   0.02802  -0.1775   0.1811   0.6041
  11.000   1.8383   0.03822   0.03115  -0.1749   0.1579   0.6073
  11.250   1.8091   0.04347   0.03618  -0.1712   0.1191   0.6093
  11.500   1.7800   0.04909   0.04169  -0.1682   0.0869   0.6113
  11.750   1.7617   0.05391   0.04649  -0.1662   0.0704   0.6141
  12.000   1.7509   0.05805   0.05064  -0.1647   0.0591   0.6175
  12.250   1.7435   0.06190   0.05453  -0.1635   0.0495   0.6211
  12.500   1.7327   0.06624   0.05886  -0.1624   0.0342   0.6248
  12.750   1.7164   0.07133   0.06390  -0.1613   0.0209   0.6282
  13.000   1.7107   0.07518   0.06783  -0.1605   0.0187   0.6331
  13.250   1.7060   0.07898   0.07175  -0.1599   0.0176   0.6376
  13.500   1.7014   0.08281   0.07570  -0.1594   0.0168   0.6429
  14.000   1.6933   0.09040   0.08353  -0.1586   0.0156   0.6544
  14.250   1.6893   0.09426   0.08752  -0.1583   0.0152   0.6612
  14.500   1.6846   0.09825   0.09164  -0.1582   0.0148   0.6683
  14.750   1.6786   0.10249   0.09601  -0.1582   0.0144   0.6766
  15.000   1.6716   0.10691   0.10056  -0.1583   0.0141   0.6858
  15.250   1.6631   0.11159   0.10538  -0.1585   0.0138   0.6972
  15.500   1.6536   0.11652   0.11046  -0.1590   0.0135   0.7124
  15.750   1.6431   0.12173   0.11583  -0.1598   0.0133   0.7378
  16.000   1.6295   0.12678   0.12121  -0.1602   0.0131   1.0000
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