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GOE 222 (MVA H.33) AIRFOIL (goe222-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 222 (MVA H.33) AIRFOIL (goe222-il)
Reynolds number: 50,000
Max Cl/Cd: 14.38 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe222-il-50000-n5.txt
Download as CSV file: xf-goe222-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 222 (MVA H.33) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.1628   0.12105   0.11386  -0.0899   0.9302   0.0801
 -10.500  -0.1601   0.11641   0.10921  -0.0931   0.9266   0.0802
 -10.250  -0.1660   0.11216   0.10497  -0.0948   0.9215   0.0805
 -10.000  -0.1779   0.10801   0.10086  -0.0956   0.9150   0.0808
  -9.750  -0.1870   0.10211   0.09497  -0.0989   0.9107   0.0810
  -9.500  -0.2054   0.09648   0.08937  -0.1007   0.9048   0.0810
  -9.250  -0.2302   0.09136   0.08429  -0.1011   0.8977   0.0808
  -9.000  -0.2617   0.08396   0.07687  -0.1046   0.8926   0.0804
  -8.750  -0.3066   0.07980   0.07274  -0.1025   0.8835   0.0798
  -8.500  -0.3405   0.06946   0.06211  -0.1126   0.8769   0.0793
  -8.250  -0.3579   0.06358   0.05590  -0.1179   0.8697   0.0794
  -8.000  -0.3493   0.05887   0.05076  -0.1234   0.8650   0.0802
  -7.750  -0.3259   0.05540   0.04686  -0.1281   0.8618   0.0817
  -7.500  -0.3043   0.05420   0.04564  -0.1290   0.8585   0.0839
  -7.250  -0.2935   0.05307   0.04441  -0.1287   0.8531   0.0859
  -7.000  -0.2692   0.05146   0.04256  -0.1306   0.8492   0.0887
  -6.750  -0.2381   0.04981   0.04058  -0.1332   0.8461   0.0915
  -6.500  -0.2084   0.04874   0.03947  -0.1348   0.8431   0.0943
  -6.250  -0.1952   0.04819   0.03890  -0.1340   0.8368   0.0972
  -6.000  -0.1650   0.04718   0.03770  -0.1361   0.8325   0.1029
  -5.750  -0.1285   0.04608   0.03659  -0.1391   0.8292   0.1101
  -5.500  -0.1030   0.04533   0.03572  -0.1404   0.8236   0.1183
  -5.250  -0.0720   0.04436   0.03484  -0.1430   0.8178   0.1313
  -5.000  -0.0281   0.04307   0.03391  -0.1480   0.8139   0.1662
  -4.750  -0.0021   0.04334   0.03454  -0.1482   0.8075   0.2124
  -4.500   0.0230   0.04397   0.03512  -0.1477   0.8003   0.2505
  -4.250   0.0598   0.04453   0.03548  -0.1487   0.7959   0.2842
  -4.000   0.0737   0.04552   0.03638  -0.1466   0.7867   0.3032
  -3.750   0.1053   0.04604   0.03670  -0.1470   0.7812   0.3259
  -3.500   0.1327   0.04668   0.03720  -0.1467   0.7755   0.3463
  -3.250   0.1438   0.04776   0.03838  -0.1430   0.7668   0.3566
  -3.000   0.1770   0.04782   0.03830  -0.1434   0.7626   0.3716
  -2.750   0.1999   0.04794   0.03820  -0.1440   0.7542   0.3835
  -2.500   0.2246   0.04806   0.03828  -0.1432   0.7480   0.3910
  -2.250   0.2659   0.04743   0.03740  -0.1459   0.7444   0.4030
  -2.000   0.2777   0.04806   0.03801  -0.1440   0.7341   0.4085
  -1.750   0.3168   0.04753   0.03719  -0.1469   0.7290   0.4193
  -1.500   0.3521   0.04702   0.03662  -0.1476   0.7257   0.4252
  -1.250   0.3632   0.04779   0.03732  -0.1462   0.7140   0.4304
  -1.000   0.4029   0.04721   0.03652  -0.1487   0.7096   0.4389
  -0.750   0.4226   0.04758   0.03686  -0.1480   0.7013   0.4434
  -0.500   0.4485   0.04769   0.03687  -0.1483   0.6936   0.4491
  -0.250   0.4892   0.04709   0.03605  -0.1508   0.6900   0.4571
   0.000   0.4986   0.04813   0.03710  -0.1490   0.6781   0.4607
   0.250   0.5316   0.04781   0.03671  -0.1498   0.6732   0.4667
   0.500   0.5723   0.04714   0.03585  -0.1519   0.6704   0.4740
   0.750   0.5771   0.04868   0.03740  -0.1500   0.6568   0.4779
   1.000   0.6116   0.04825   0.03691  -0.1508   0.6535   0.4841
   1.250   0.6176   0.04990   0.03855  -0.1493   0.6408   0.4889
   1.500   0.6527   0.04957   0.03807  -0.1505   0.6370   0.4959
   2.000   0.6891   0.05111   0.03956  -0.1493   0.6210   0.5067
   2.250   0.7252   0.05064   0.03898  -0.1503   0.6184   0.5150
   2.500   0.7229   0.05319   0.04159  -0.1483   0.6057   0.5189
   2.750   0.7557   0.05292   0.04124  -0.1488   0.6028   0.5268
   3.000   0.7561   0.05550   0.04382  -0.1474   0.5911   0.5322
   3.250   0.7851   0.05539   0.04371  -0.1474   0.5878   0.5396
   3.750   0.8108   0.05847   0.04680  -0.1461   0.5735   0.5542
   4.000   0.8405   0.05845   0.04675  -0.1463   0.5709   0.5641
   4.500   0.8604   0.06217   0.05055  -0.1446   0.5566   0.5801
   4.750   0.8906   0.06200   0.05039  -0.1448   0.5542   0.5922
   5.250   0.9025   0.06673   0.05527  -0.1429   0.5400   0.6116
   5.500   0.9326   0.06650   0.05509  -0.1429   0.5376   0.6276
   6.000   0.9435   0.07119   0.05999  -0.1409   0.5229   0.6556
   6.250   0.9780   0.06998   0.05893  -0.1407   0.5205   0.6839
   6.750   0.9910   0.07192   0.06144  -0.1364   0.5045   0.8369
   7.250   1.0133   0.07482   0.06427  -0.1347   0.4882   1.0000
   7.500   1.0504   0.07359   0.06294  -0.1347   0.4860   1.0000
   8.000   1.0602   0.07866   0.06804  -0.1330   0.4695   1.0000
   8.500   1.0698   0.08372   0.07315  -0.1313   0.4529   1.0000
   8.750   1.1032   0.08265   0.07204  -0.1309   0.4505   1.0000
   9.250   1.1123   0.08758   0.07707  -0.1291   0.4332   1.0000
   9.750   1.1209   0.09264   0.08223  -0.1275   0.4159   1.0000
  10.250   1.1304   0.09760   0.08730  -0.1261   0.3984   1.0000
  10.500   1.1605   0.09657   0.08627  -0.1253   0.3958   1.0000
  10.750   1.1398   0.10261   0.09241  -0.1249   0.3809   1.0000
  11.000   1.1689   0.10165   0.09147  -0.1240   0.3786   1.0000
  11.250   1.1449   0.10855   0.09847  -0.1242   0.3639   1.0000
  11.750   1.1480   0.11496   0.10500  -0.1239   0.3475   1.0000
  12.250   1.1481   0.12208   0.11224  -0.1242   0.3319   1.0000
  12.500   1.1704   0.12211   0.11231  -0.1235   0.3294   1.0000
  12.750   1.1444   0.13019   0.12047  -0.1253   0.3174   1.0000
  13.000   1.1661   0.13027   0.12061  -0.1246   0.3148   1.0000
  13.500   1.1577   0.13945   0.12992  -0.1266   0.3010   1.0000
  13.750   1.1775   0.13986   0.13038  -0.1261   0.2986   1.0000
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