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GOE 182 (MVA H.27) AIRFOIL (goe182-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 182 (MVA H.27) AIRFOIL (goe182-il)
Reynolds number: 100,000
Max Cl/Cd: 48.56 at α=11°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe182-il-100000.txt
Download as CSV file: xf-goe182-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 182 (MVA H.27) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2998   0.10273   0.09796  -0.0182   1.0000   0.0825
  -8.000  -0.3080   0.10236   0.09770  -0.0221   1.0000   0.0844
  -7.750  -0.3152   0.10207   0.09753  -0.0293   1.0000   0.0850
  -7.500  -0.3009   0.09549   0.09097  -0.0234   1.0000   0.0864
  -7.250  -0.2874   0.09174   0.08723  -0.0211   1.0000   0.0886
  -7.000  -0.2820   0.08920   0.08475  -0.0208   1.0000   0.0912
  -6.750  -0.2799   0.08701   0.08264  -0.0216   1.0000   0.0946
  -6.500  -0.2835   0.08665   0.08238  -0.0319   1.0000   0.0985
  -6.250  -0.2812   0.08262   0.07843  -0.0292   1.0000   0.0999
  -6.000  -0.2769   0.07985   0.07573  -0.0241   1.0000   0.1022
  -5.750  -0.2758   0.07789   0.07386  -0.0225   1.0000   0.1050
  -5.500  -0.2789   0.07632   0.07237  -0.0222   1.0000   0.1082
  -5.000  -0.2665   0.07144   0.06755  -0.0299   0.9965   0.1148
  -4.750  -0.2174   0.06733   0.06335  -0.0387   0.9870   0.1252
  -4.500  -0.1736   0.06245   0.05842  -0.0457   0.9768   0.1328
  -4.250  -0.1152   0.05743   0.05324  -0.0582   0.9654   0.1456
  -4.000  -0.0560   0.05280   0.04843  -0.0693   0.9559   0.1602
  -3.750  -0.0074   0.04903   0.04455  -0.0765   0.9433   0.1759
  -3.500   0.0366   0.04567   0.04110  -0.0817   0.9301   0.1924
  -3.250   0.0790   0.04250   0.03782  -0.0863   0.9152   0.2087
  -3.000   0.1277   0.04071   0.03568  -0.0926   0.8980   0.2376
  -2.750   0.1967   0.02970   0.02323  -0.1039   0.8845   0.1268
  -2.500   0.2350   0.02564   0.01843  -0.1056   0.8671   0.1130
  -2.250   0.2671   0.02342   0.01591  -0.1058   0.8480   0.1113
  -2.000   0.2972   0.02176   0.01384  -0.1053   0.8262   0.1112
  -1.750   0.3260   0.02050   0.01223  -0.1047   0.8044   0.1146
  -1.500   0.3537   0.01961   0.01113  -0.1037   0.7833   0.1183
  -1.250   0.3808   0.01885   0.01010  -0.1027   0.7601   0.1222
  -1.000   0.4080   0.01821   0.00916  -0.1016   0.7385   0.1283
  -0.750   0.4341   0.01784   0.00869  -0.1006   0.7164   0.1397
  -0.500   0.4601   0.01736   0.00814  -0.0996   0.6934   0.1529
  -0.250   0.4862   0.01693   0.00765  -0.0985   0.6716   0.1767
   0.000   0.5116   0.01644   0.00729  -0.0976   0.6469   0.2226
   0.250   0.5376   0.01560   0.00693  -0.0967   0.6240   0.3689
   0.500   0.5649   0.01409   0.00660  -0.0957   0.5978   1.0000
   0.750   0.5911   0.01435   0.00642  -0.0948   0.5730   1.0000
   1.000   0.6171   0.01466   0.00636  -0.0940   0.5479   1.0000
   1.250   0.6431   0.01505   0.00642  -0.0933   0.5246   1.0000
   1.500   0.6691   0.01547   0.00655  -0.0927   0.5029   1.0000
   1.750   0.6953   0.01591   0.00671  -0.0922   0.4845   1.0000
   2.000   0.7217   0.01635   0.00693  -0.0917   0.4683   1.0000
   2.250   0.7481   0.01679   0.00719  -0.0913   0.4541   1.0000
   2.500   0.7746   0.01725   0.00749  -0.0909   0.4420   1.0000
   2.750   0.8014   0.01773   0.00776  -0.0905   0.4325   1.0000
   3.000   0.8280   0.01819   0.00817  -0.0902   0.4229   1.0000
   3.250   0.8550   0.01872   0.00855  -0.0900   0.4159   1.0000
   3.500   0.8816   0.01923   0.00906  -0.0897   0.4086   1.0000
   3.750   0.9087   0.01978   0.00947  -0.0895   0.4034   1.0000
   4.000   0.9351   0.02038   0.01011  -0.0893   0.3980   1.0000
   4.250   0.9616   0.02097   0.01072  -0.0890   0.3931   1.0000
   4.500   0.9885   0.02158   0.01127  -0.0888   0.3893   1.0000
   4.750   1.0154   0.02228   0.01193  -0.0887   0.3861   1.0000
   5.000   1.0408   0.02302   0.01283  -0.0884   0.3826   1.0000
   5.250   1.0665   0.02376   0.01368  -0.0882   0.3792   1.0000
   5.500   1.0924   0.02447   0.01445  -0.0880   0.3761   1.0000
   5.750   1.1185   0.02521   0.01521  -0.0878   0.3735   1.0000
   6.000   1.1449   0.02608   0.01607  -0.0876   0.3715   1.0000
   6.250   1.1686   0.02710   0.01734  -0.0873   0.3695   1.0000
   6.500   1.1919   0.02821   0.01868  -0.0870   0.3676   1.0000
   6.750   1.2149   0.02938   0.02007  -0.0866   0.3659   1.0000
   7.000   1.2375   0.03063   0.02154  -0.0863   0.3643   1.0000
   7.250   1.2599   0.03189   0.02300  -0.0859   0.3626   1.0000
   7.500   1.2825   0.03309   0.02437  -0.0855   0.3607   1.0000
   7.750   1.3057   0.03424   0.02565  -0.0852   0.3589   1.0000
   8.000   1.3306   0.03523   0.02671  -0.0849   0.3565   1.0000
   8.250   1.3458   0.03700   0.02882  -0.0839   0.3530   1.0000
   8.500   1.3620   0.03833   0.03042  -0.0829   0.3476   1.0000
   8.750   1.3976   0.03738   0.02922  -0.0828   0.3408   1.0000
   9.000   1.4075   0.03919   0.03149  -0.0814   0.3353   1.0000
   9.250   1.4355   0.03880   0.03108  -0.0808   0.3279   1.0000
   9.500   1.4547   0.03919   0.03163  -0.0796   0.3199   1.0000
   9.750   1.4874   0.03743   0.02968  -0.0789   0.3072   1.0000
  10.000   1.5134   0.03630   0.02850  -0.0779   0.2950   1.0000
  10.250   1.5290   0.03628   0.02875  -0.0762   0.2844   1.0000
  10.500   1.5494   0.03513   0.02765  -0.0745   0.2699   1.0000
  10.750   1.5675   0.03299   0.02538  -0.0720   0.2480   1.0000
  11.000   1.5660   0.03225   0.02496  -0.0678   0.2184   1.0000
  11.250   1.5511   0.03348   0.02595  -0.0632   0.1275   1.0000
  11.500   1.5267   0.03708   0.02925  -0.0589   0.1076   1.0000
  11.750   1.5056   0.04106   0.03327  -0.0564   0.0965   1.0000
  12.000   1.4841   0.04576   0.03806  -0.0555   0.0908   1.0000
  12.250   1.4661   0.05081   0.04330  -0.0560   0.0855   1.0000
  12.500   1.4452   0.05678   0.04943  -0.0575   0.0828   1.0000
  12.750   1.4224   0.06347   0.05628  -0.0597   0.0813   1.0000
  13.000   1.3989   0.07058   0.06353  -0.0621   0.0804   1.0000
  13.250   1.3761   0.07761   0.07066  -0.0644   0.0793   1.0000
  13.500   1.3583   0.08383   0.07697  -0.0662   0.0772   1.0000
  13.750   1.3441   0.08941   0.08263  -0.0676   0.0744   1.0000
  14.000   1.3333   0.09436   0.08761  -0.0687   0.0715   1.0000
  14.250   1.3336   0.09667   0.08975  -0.0678   0.0676   1.0000
  14.500   1.3409   0.09815   0.09129  -0.0664   0.0637   1.0000
  14.750   1.3747   0.09346   0.08622  -0.0593   0.0573   1.0000
  15.000   1.3877   0.09445   0.08735  -0.0572   0.0551   1.0000
  15.250   1.4032   0.09513   0.08811  -0.0546   0.0530   1.0000
  15.500   1.4153   0.09657   0.08960  -0.0527   0.0510   1.0000
  15.750   1.4500   0.09568   0.08855  -0.0467   0.0477   1.0000
  16.000   1.4413   0.10041   0.09353  -0.0482   0.0474   1.0000
  16.250   1.4325   0.10542   0.09881  -0.0499   0.0471   1.0000
  16.500   1.4227   0.11075   0.10439  -0.0519   0.0469   1.0000
  16.750   1.4104   0.11663   0.11050  -0.0546   0.0469   1.0000
  17.000   1.3962   0.12302   0.11713  -0.0578   0.0469   1.0000
  17.250   1.3806   0.12992   0.12425  -0.0617   0.0471   1.0000
  17.500   1.3636   0.13741   0.13195  -0.0662   0.0473   1.0000
  17.750   1.3456   0.14548   0.14022  -0.0713   0.0475   1.0000
  18.000   1.3275   0.15396   0.14885  -0.0767   0.0478   1.0000
  18.250   1.2970   0.16606   0.16123  -0.0865   0.0487   1.0000
  18.500   1.1921   0.20748   0.20281  -0.1152   0.0578   1.0000
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