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GOE 244 (MVA PR.4) AIRFOIL (goe244-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 244 (MVA PR.4) AIRFOIL (goe244-il)
Reynolds number: 500,000
Max Cl/Cd: 92.31 at α=-0.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe244-il-500000.txt
Download as CSV file: xf-goe244-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 244 (MVA PR.4) 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   0.2424   0.10246   0.09939  -0.1226   0.8420   0.0312
 -10.250   0.2522   0.10000   0.09690  -0.1239   0.8359   0.0320
 -10.000   0.2440   0.09554   0.09238  -0.1294   0.8303   0.0334
  -9.750   0.2563   0.09287   0.08971  -0.1298   0.8247   0.0336
  -9.500   0.2718   0.09088   0.08772  -0.1298   0.8187   0.0338
  -9.250   0.2858   0.08898   0.08576  -0.1301   0.8129   0.0340
  -9.000   0.2987   0.08702   0.08379  -0.1308   0.8068   0.0343
  -8.750   0.3108   0.08498   0.08175  -0.1318   0.8004   0.0348
  -8.500   0.3223   0.08282   0.07955  -0.1329   0.7949   0.0354
  -8.250   0.3330   0.08049   0.07719  -0.1344   0.7894   0.0363
  -8.000   0.3263   0.07495   0.07166  -0.1410   0.7829   0.0380
  -7.750   0.3414   0.07332   0.06999  -0.1407   0.7767   0.0382
  -7.500   0.3567   0.07181   0.06845  -0.1409   0.7705   0.0385
  -7.250   0.3713   0.07020   0.06685  -0.1414   0.7635   0.0389
  -7.000   0.3848   0.06843   0.06503  -0.1423   0.7570   0.0396
  -6.750   0.3769   0.06210   0.05872  -0.1508   0.7505   0.0428
  -6.500   0.3925   0.06082   0.05744  -0.1502   0.7442   0.0431
  -6.250   0.4092   0.05958   0.05615  -0.1503   0.7385   0.0434
  -6.000   0.4255   0.05114   0.04769  -0.1670   0.7327   0.0480
  -5.750   0.4412   0.05059   0.04716  -0.1651   0.7265   0.0483
  -5.500   0.4598   0.04982   0.04635  -0.1647   0.7205   0.0486
  -5.250   0.4796   0.04881   0.04532  -0.1653   0.7146   0.0491
  -5.000   0.5007   0.04727   0.04378  -0.1673   0.7078   0.0501
  -4.750   0.6781   0.01801   0.01260  -0.2458   0.7016   0.0438
  -4.500   0.7148   0.01636   0.01070  -0.2482   0.6953   0.0407
  -4.250   0.7511   0.01505   0.00910  -0.2503   0.6884   0.0394
  -4.000   0.7834   0.01443   0.00831  -0.2513   0.6817   0.0392
  -3.750   0.8146   0.01396   0.00777  -0.2520   0.6750   0.0393
  -3.500   0.8453   0.01358   0.00733  -0.2526   0.6674   0.0395
  -3.250   0.8757   0.01329   0.00695  -0.2531   0.6603   0.0397
  -3.000   0.9061   0.01301   0.00665  -0.2536   0.6522   0.0400
  -2.750   0.9358   0.01283   0.00638  -0.2540   0.6436   0.0404
  -2.500   0.9657   0.01264   0.00617  -0.2544   0.6347   0.0409
  -2.250   0.9946   0.01255   0.00600  -0.2546   0.6247   0.0418
  -2.000   1.0238   0.01245   0.00586  -0.2549   0.6145   0.0425
  -1.750   1.0525   0.01238   0.00569  -0.2551   0.6035   0.0431
  -1.500   1.0814   0.01228   0.00555  -0.2554   0.5909   0.0441
  -1.250   1.1088   0.01230   0.00549  -0.2553   0.5771   0.0453
  -1.000   1.1344   0.01239   0.00547  -0.2549   0.5607   0.0468
  -0.750   1.1585   0.01255   0.00551  -0.2543   0.5407   0.0488
  -0.500   1.1803   0.01280   0.00564  -0.2532   0.5166   0.0525
  -0.250   1.1997   0.01316   0.00587  -0.2517   0.4918   0.0636
   0.000   1.2197   0.01349   0.00610  -0.2503   0.4704   0.0900
   0.250   1.2424   0.01364   0.00642  -0.2499   0.4536   0.2154
   0.500   1.2602   0.01400   0.00674  -0.2481   0.4408   0.2417
   0.750   1.2784   0.01434   0.00705  -0.2464   0.4311   0.2613
   1.000   1.2971   0.01475   0.00740  -0.2449   0.4222   0.2768
   1.250   1.3182   0.01511   0.00774  -0.2438   0.4150   0.2934
   1.500   1.3401   0.01544   0.00807  -0.2429   0.4086   0.3094
   1.750   1.3601   0.01586   0.00847  -0.2416   0.4027   0.3282
   2.000   1.3812   0.01624   0.00887  -0.2406   0.3977   0.3535
   2.250   1.4038   0.01654   0.00923  -0.2399   0.3934   0.3828
   2.500   1.4247   0.01693   0.00966  -0.2388   0.3890   0.4153
   2.750   1.4438   0.01742   0.01013  -0.2374   0.3849   0.4398
   3.000   1.4615   0.01800   0.01068  -0.2359   0.3805   0.4554
   3.250   1.4835   0.01834   0.01104  -0.2350   0.3779   0.4690
   3.500   1.5048   0.01872   0.01144  -0.2340   0.3749   0.4815
   3.750   1.5251   0.01915   0.01189  -0.2329   0.3719   0.4928
   4.000   1.5442   0.01966   0.01236  -0.2317   0.3689   0.5036
   4.250   1.5629   0.02019   0.01289  -0.2304   0.3660   0.5123
   4.500   1.5812   0.02079   0.01344  -0.2291   0.3626   0.5213
   4.750   1.6017   0.02123   0.01392  -0.2281   0.3606   0.5292
   5.000   1.6218   0.02167   0.01440  -0.2271   0.3583   0.5362
   5.250   1.6413   0.02215   0.01489  -0.2261   0.3554   0.5429
   5.500   1.6602   0.02266   0.01542  -0.2250   0.3521   0.5489
   5.750   1.6777   0.02327   0.01602  -0.2237   0.3491   0.5551
   6.000   1.6947   0.02394   0.01666  -0.2223   0.3461   0.5612
   6.250   1.7133   0.02454   0.01725  -0.2212   0.3431   0.5672
   6.500   1.7321   0.02506   0.01785  -0.2202   0.3413   0.5739
   6.750   1.7503   0.02564   0.01847  -0.2191   0.3391   0.5809
   7.000   1.7685   0.02622   0.01910  -0.2181   0.3370   0.5871
   7.250   1.7866   0.02682   0.01975  -0.2170   0.3350   0.5945
   7.500   1.8041   0.02747   0.02042  -0.2159   0.3331   0.6031
   7.750   1.8209   0.02816   0.02115  -0.2147   0.3312   0.6139
   8.000   1.8373   0.02889   0.02189  -0.2135   0.3290   0.6252
   8.250   1.8550   0.02955   0.02255  -0.2124   0.3263   0.6364
   8.500   1.8721   0.03023   0.02331  -0.2114   0.3245   0.6461
   8.750   1.8878   0.03100   0.02416  -0.2102   0.3227   0.6572
   9.000   1.9042   0.03175   0.02500  -0.2092   0.3209   0.6711
   9.250   1.9208   0.03249   0.02584  -0.2082   0.3189   0.6908
   9.500   1.9367   0.03329   0.02675  -0.2072   0.3169   0.7226
   9.750   1.9489   0.03386   0.02757  -0.2055   0.3150   1.0000
  10.000   1.9640   0.03475   0.02845  -0.2044   0.3130   1.0000
  10.250   1.9787   0.03565   0.02934  -0.2032   0.3108   1.0000
  10.500   1.9947   0.03645   0.03011  -0.2021   0.3080   1.0000
  10.750   2.0070   0.03759   0.03133  -0.2010   0.3063   1.0000
  11.000   2.0197   0.03871   0.03253  -0.1998   0.3039   1.0000
  11.250   2.0311   0.03996   0.03384  -0.1987   0.3010   1.0000
  11.500   2.0425   0.04121   0.03511  -0.1975   0.2981   1.0000
  11.750   2.0524   0.04258   0.03649  -0.1962   0.2951   1.0000
  12.000   2.0628   0.04386   0.03773  -0.1948   0.2917   1.0000
  12.250   2.0740   0.04521   0.03919  -0.1938   0.2894   1.0000
  12.500   2.0841   0.04670   0.04076  -0.1928   0.2864   1.0000
  12.750   2.0944   0.04815   0.04228  -0.1917   0.2833   1.0000
  13.000   2.1028   0.04978   0.04394  -0.1906   0.2801   1.0000
  13.250   2.1085   0.05164   0.04580  -0.1892   0.2764   1.0000
  13.500   2.1165   0.05335   0.04758  -0.1882   0.2729   1.0000
  13.750   2.1251   0.05508   0.04940  -0.1873   0.2688   1.0000
  14.000   2.1305   0.05710   0.05146  -0.1862   0.2641   1.0000
  14.250   2.1312   0.05961   0.05397  -0.1848   0.2595   1.0000
  14.500   2.1393   0.06142   0.05589  -0.1840   0.2548   1.0000
  14.750   2.1416   0.06386   0.05838  -0.1829   0.2486   1.0000
  15.000   2.1396   0.06676   0.06130  -0.1817   0.2423   1.0000
  15.250   2.1388   0.06959   0.06417  -0.1806   0.2332   1.0000
  15.500   2.1314   0.07318   0.06778  -0.1794   0.2229   1.0000
  15.750   2.1161   0.07778   0.07236  -0.1779   0.2096   1.0000
  16.000   2.0937   0.08328   0.07783  -0.1765   0.1953   1.0000
  16.250   2.0683   0.08925   0.08379  -0.1752   0.1837   1.0000
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