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GOE 278 (DAIMLER IX) AIRFOIL (goe278-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 278 (DAIMLER IX) AIRFOIL (goe278-il)
Reynolds number: 50,000
Max Cl/Cd: 38.49 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe278-il-50000.txt
Download as CSV file: xf-goe278-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 278 (DAIMLER IX) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3886   0.11938   0.11216  -0.0179   1.0000   0.1079
  -9.250  -0.3912   0.11805   0.11091  -0.0201   1.0000   0.1110
  -9.000  -0.4002   0.11785   0.11084  -0.0231   1.0000   0.1120
  -8.750  -0.3772   0.11038   0.10331  -0.0203   1.0000   0.1182
  -8.500  -0.3765   0.10812   0.10113  -0.0213   1.0000   0.1234
  -8.250  -0.3869   0.10760   0.10075  -0.0234   1.0000   0.1258
  -8.000  -0.3749   0.10251   0.09570  -0.0221   1.0000   0.1303
  -7.750  -0.3722   0.09977   0.09302  -0.0218   1.0000   0.1362
  -7.500  -0.3803   0.09876   0.09214  -0.0246   1.0000   0.1400
  -7.250  -0.3764   0.09498   0.08845  -0.0241   1.0000   0.1435
  -7.000  -0.3705   0.09182   0.08533  -0.0228   1.0000   0.1509
  -6.750  -0.3782   0.09147   0.08506  -0.0290   1.0000   0.1557
  -6.500  -0.3675   0.08628   0.07995  -0.0231   1.0000   0.1630
  -6.250  -0.3711   0.08575   0.07943  -0.0299   1.0000   0.1709
  -6.000  -0.3630   0.08092   0.07470  -0.0233   1.0000   0.1801
  -5.750  -0.3606   0.07816   0.07198  -0.0237   1.0000   0.1904
  -5.500  -0.3571   0.07550   0.06937  -0.0238   1.0000   0.2046
  -5.250  -0.3526   0.07271   0.06664  -0.0223   1.0000   0.2214
  -5.000  -0.3478   0.07014   0.06410  -0.0210   1.0000   0.2423
  -4.750  -0.3432   0.06742   0.06143  -0.0202   1.0000   0.2663
  -4.500   0.0258   0.04142   0.03453  -0.0279   1.0000   1.0000
  -4.250   0.0357   0.03968   0.03285  -0.0284   1.0000   1.0000
  -4.000   0.0451   0.03802   0.03126  -0.0289   1.0000   1.0000
  -3.750   0.0537   0.03647   0.02979  -0.0291   1.0000   1.0000
  -3.500   0.0615   0.03502   0.02842  -0.0292   1.0000   1.0000
  -3.250   0.0223   0.03599   0.02961  -0.0182   1.0000   0.9815
  -3.000  -0.0274   0.03712   0.03099  -0.0056   1.0000   0.9566
  -2.750  -0.0734   0.03765   0.03175   0.0054   1.0000   0.9309
  -2.500  -0.1213   0.03802   0.03235   0.0164   1.0000   0.9120
  -2.250  -0.1746   0.03826   0.03284   0.0279   1.0000   0.8929
  -2.000  -0.2668   0.03925   0.03416   0.0460   1.0000   0.8635
  -1.750  -0.3187   0.03854   0.03367   0.0530   1.0000   0.8267
  -1.500  -0.3099   0.03648   0.03162   0.0439   1.0000   0.7840
  -1.250   0.0154   0.03256   0.02371  -0.0502   1.0000   0.2433
  -1.000   0.0480   0.03162   0.02226  -0.0511   1.0000   0.2123
  -0.750   0.0764   0.03083   0.02112  -0.0515   1.0000   0.1944
  -0.500   0.1025   0.03056   0.02043  -0.0514   1.0000   0.1848
  -0.250   0.1265   0.02996   0.01969  -0.0516   1.0000   0.1803
   0.000   0.1498   0.02987   0.01933  -0.0515   1.0000   0.1727
   0.250   0.1710   0.02988   0.01920  -0.0514   1.0000   0.1685
   0.500   0.2293   0.02963   0.01870  -0.0572   0.9868   0.1641
   0.750   0.2942   0.02943   0.01830  -0.0639   0.9694   0.1661
   1.000   0.3518   0.02913   0.01798  -0.0696   0.9489   0.1744
   1.250   0.4145   0.02880   0.01763  -0.0759   0.9287   0.1857
   1.500   0.4663   0.02830   0.01741  -0.0803   0.9045   0.2178
   1.750   0.5195   0.02633   0.01709  -0.0835   0.8838   1.0000
   2.000   0.5663   0.02637   0.01669  -0.0857   0.8576   1.0000
   2.250   0.6141   0.02612   0.01622  -0.0880   0.8334   1.0000
   2.500   0.6577   0.02575   0.01574  -0.0892   0.8092   1.0000
   2.750   0.6923   0.02558   0.01551  -0.0891   0.7833   1.0000
   3.000   0.7323   0.02511   0.01496  -0.0893   0.7623   1.0000
   3.250   0.7603   0.02522   0.01505  -0.0884   0.7373   1.0000
   3.500   0.7948   0.02500   0.01477  -0.0879   0.7179   1.0000
   3.750   0.8197   0.02549   0.01525  -0.0869   0.6956   1.0000
   4.000   0.8487   0.02574   0.01547  -0.0862   0.6770   1.0000
   4.250   0.8775   0.02607   0.01580  -0.0855   0.6597   1.0000
   4.500   0.9032   0.02662   0.01635  -0.0845   0.6414   1.0000
   4.750   0.9268   0.02735   0.01713  -0.0835   0.6230   1.0000
   5.000   0.9511   0.02810   0.01795  -0.0825   0.6060   1.0000
   5.250   0.9750   0.02894   0.01886  -0.0816   0.5901   1.0000
   5.500   0.9984   0.02989   0.01992  -0.0807   0.5753   1.0000
   5.750   1.0213   0.03093   0.02108  -0.0799   0.5612   1.0000
   6.000   1.0439   0.03193   0.02225  -0.0789   0.5466   1.0000
   6.250   1.0665   0.03255   0.02298  -0.0774   0.5283   1.0000
   6.500   1.0925   0.03222   0.02260  -0.0752   0.5044   1.0000
   6.750   1.1147   0.03214   0.02256  -0.0730   0.4799   1.0000
   7.000   1.1372   0.03229   0.02280  -0.0711   0.4584   1.0000
   7.250   1.1584   0.03244   0.02307  -0.0691   0.4360   1.0000
   7.500   1.1780   0.03208   0.02274  -0.0665   0.4071   1.0000
   7.750   1.1958   0.03135   0.02189  -0.0634   0.3716   1.0000
   8.000   1.2046   0.03130   0.02202  -0.0595   0.3296   1.0000
   8.250   1.2029   0.03168   0.02228  -0.0542   0.2647   1.0000
   8.500   1.2010   0.03331   0.02341  -0.0497   0.2015   1.0000
   8.750   1.2082   0.03543   0.02509  -0.0469   0.1711   1.0000
   9.000   1.2234   0.03775   0.02715  -0.0450   0.1531   1.0000
   9.250   1.2457   0.04015   0.02942  -0.0439   0.1404   1.0000
   9.500   1.2641   0.04244   0.03201  -0.0425   0.1302   1.0000
   9.750   1.2860   0.04520   0.03492  -0.0416   0.1229   1.0000
  10.000   1.3064   0.04809   0.03805  -0.0405   0.1174   1.0000
  10.250   1.3238   0.05134   0.04145  -0.0394   0.1124   1.0000
  10.500   1.3292   0.05474   0.04537  -0.0372   0.1092   1.0000
  10.750   1.3334   0.05862   0.04969  -0.0350   0.1077   1.0000
  11.000   1.3314   0.06270   0.05418  -0.0327   0.1067   1.0000
  11.250   1.3232   0.06681   0.05870  -0.0302   0.1060   1.0000
  11.500   1.3047   0.07098   0.06321  -0.0274   0.1060   1.0000
  11.750   1.2753   0.07573   0.06825  -0.0250   0.1071   1.0000
  12.000   1.2417   0.08147   0.07425  -0.0246   0.1086   1.0000
  12.250   1.2078   0.08830   0.08128  -0.0262   0.1103   1.0000
  12.500   1.1756   0.09619   0.08930  -0.0295   0.1119   1.0000
  12.750   1.1492   0.10466   0.09783  -0.0335   0.1132   1.0000
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