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GOE 223 (MVA H.34) AIRFOIL (goe223-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 223 (MVA H.34) AIRFOIL (goe223-il)
Reynolds number: 50,000
Max Cl/Cd: 15.83 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe223-il-50000-n5.txt
Download as CSV file: xf-goe223-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 223 (MVA H.34) 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  -0.2596   0.10927   0.10280  -0.0745   0.9678   0.0681
 -10.500  -0.2598   0.10240   0.09593  -0.0797   0.9615   0.0675
 -10.250  -0.2695   0.09417   0.08767  -0.0859   0.9552   0.0666
 -10.000  -0.2948   0.08486   0.07830  -0.0931   0.9468   0.0654
  -9.750  -0.3313   0.07647   0.06979  -0.0996   0.9356   0.0643
  -9.500  -0.3672   0.07000   0.06311  -0.1047   0.9231   0.0635
  -9.250  -0.3783   0.06390   0.05666  -0.1121   0.9131   0.0633
  -9.000  -0.3851   0.06053   0.05304  -0.1136   0.9021   0.0635
  -8.750  -0.3664   0.05686   0.04902  -0.1180   0.8966   0.0649
  -8.500  -0.3629   0.05456   0.04648  -0.1179   0.8861   0.0661
  -8.250  -0.3359   0.05144   0.04291  -0.1216   0.8810   0.0679
  -8.000  -0.3252   0.04959   0.04077  -0.1209   0.8711   0.0688
  -7.750  -0.2937   0.04739   0.03820  -0.1228   0.8660   0.0699
  -7.500  -0.2757   0.04613   0.03685  -0.1216   0.8575   0.0710
  -7.250  -0.2470   0.04491   0.03562  -0.1220   0.8514   0.0735
  -7.000  -0.2198   0.04382   0.03439  -0.1221   0.8450   0.0764
  -6.750  -0.1991   0.04297   0.03342  -0.1210   0.8363   0.0787
  -6.500  -0.1653   0.04194   0.03220  -0.1214   0.8318   0.0810
  -6.250  -0.1524   0.04139   0.03168  -0.1193   0.8209   0.0828
  -6.000  -0.1207   0.04028   0.03054  -0.1203   0.8157   0.0864
  -5.750  -0.1046   0.03966   0.02985  -0.1194   0.8050   0.0905
  -5.500  -0.0720   0.03843   0.02855  -0.1213   0.7993   0.0970
  -5.250  -0.0522   0.03757   0.02764  -0.1216   0.7889   0.1036
  -5.000  -0.0168   0.03589   0.02593  -0.1250   0.7829   0.1160
  -4.750   0.0131   0.03385   0.02420  -0.1289   0.7737   0.1509
  -4.500   0.0430   0.03408   0.02538  -0.1293   0.7664   0.3406
  -4.250   0.0677   0.03500   0.02606  -0.1284   0.7570   0.3823
  -4.000   0.0949   0.03595   0.02684  -0.1273   0.7495   0.4135
  -3.750   0.1160   0.03674   0.02752  -0.1253   0.7409   0.4316
  -3.500   0.1395   0.03734   0.02800  -0.1237   0.7331   0.4489
  -3.250   0.1664   0.03777   0.02830  -0.1224   0.7274   0.4660
  -3.000   0.1809   0.03847   0.02895  -0.1198   0.7172   0.4790
  -2.750   0.2106   0.03850   0.02887  -0.1187   0.7132   0.4911
  -2.500   0.2292   0.03863   0.02880  -0.1193   0.7024   0.4997
  -2.250   0.2603   0.03826   0.02827  -0.1196   0.6981   0.5034
  -2.000   0.2786   0.03848   0.02838  -0.1191   0.6894   0.5071
  -1.750   0.3093   0.03818   0.02788  -0.1204   0.6837   0.5125
  -1.500   0.3481   0.03754   0.02699  -0.1229   0.6804   0.5182
  -1.250   0.3585   0.03827   0.02769  -0.1213   0.6707   0.5212
  -1.000   0.3890   0.03806   0.02734  -0.1221   0.6665   0.5256
  -0.750   0.4265   0.03761   0.02668  -0.1242   0.6638   0.5316
  -0.500   0.4349   0.03870   0.02773  -0.1231   0.6541   0.5357
  -0.250   0.4644   0.03861   0.02755  -0.1235   0.6503   0.5398
   0.000   0.5001   0.03825   0.02706  -0.1249   0.6477   0.5450
   0.250   0.5032   0.03979   0.02857  -0.1233   0.6382   0.5495
   0.500   0.5324   0.03989   0.02858  -0.1241   0.6346   0.5545
   0.750   0.5654   0.03974   0.02837  -0.1249   0.6322   0.5595
   1.250   0.5916   0.04206   0.03058  -0.1238   0.6192   0.5697
   1.500   0.6225   0.04201   0.03050  -0.1242   0.6167   0.5746
   2.000   0.6411   0.04546   0.03394  -0.1228   0.6041   0.5847
   2.250   0.6703   0.04564   0.03407  -0.1233   0.6013   0.5904
   2.500   0.7028   0.04550   0.03389  -0.1239   0.5993   0.5967
   3.000   0.7121   0.05035   0.03880  -0.1224   0.5857   0.6075
   3.250   0.7431   0.05022   0.03866  -0.1227   0.5835   0.6146
   3.750   0.7546   0.05489   0.04339  -0.1213   0.5693   0.6262
   4.000   0.7902   0.05421   0.04270  -0.1217   0.5670   0.6353
   4.500   0.8081   0.05785   0.04643  -0.1200   0.5520   0.6497
   4.750   0.8280   0.05857   0.04718  -0.1196   0.5461   0.6591
   5.250   0.8743   0.05889   0.04757  -0.1185   0.5339   0.6800
   5.750   0.8999   0.06124   0.05006  -0.1167   0.5180   0.7029
   6.000   0.8999   0.06386   0.05279  -0.1155   0.5087   0.7135
   6.250   0.9156   0.06484   0.05387  -0.1148   0.5023   0.7285
   6.500   0.9479   0.06385   0.05300  -0.1143   0.4993   0.7503
   6.750   0.9842   0.06216   0.05147  -0.1136   0.4973   0.7811
   7.250   0.9413   0.07081   0.06058  -0.1091   0.4713   0.8896
   7.500   0.9683   0.07055   0.06031  -0.1090   0.4659   1.0000
   7.750   1.0085   0.06901   0.05869  -0.1091   0.4631   1.0000
   8.250   0.9893   0.07680   0.06657  -0.1075   0.4360   1.0000
   8.500   1.0192   0.07608   0.06584  -0.1071   0.4311   1.0000
   9.000   1.0431   0.07870   0.06849  -0.1058   0.4136   1.0000
   9.500   1.0608   0.08220   0.07208  -0.1046   0.3961   1.0000
  10.500   1.0540   0.09595   0.08604  -0.1037   0.3563   1.0000
  10.750   1.0741   0.09647   0.08662  -0.1032   0.3526   1.0000
  11.250   1.0829   0.10194   0.09220  -0.1030   0.3383   1.0000
  11.750   1.0892   0.10794   0.09833  -0.1031   0.3245   1.0000
  12.000   1.1132   0.10760   0.09806  -0.1024   0.3219   1.0000
  12.500   1.1102   0.11544   0.10606  -0.1033   0.3086   1.0000
  13.000   1.1168   0.12131   0.11208  -0.1038   0.2948   1.0000
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