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GOE 144 (MVA H.21) AIRFOIL (goe144-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 144 (MVA H.21) AIRFOIL (goe144-il)
Reynolds number: 1,000,000
Max Cl/Cd: 95.41 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe144-il-1000000-n5.txt
Download as CSV file: xf-goe144-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 144 (MVA H.21) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3930   0.10139   0.09979  -0.0238   1.0000   0.0042
  -9.750  -0.4031   0.09569   0.09412  -0.0254   1.0000   0.0045
  -9.250  -0.5013   0.04529   0.04331  -0.0794   0.9800   0.0046
  -9.000  -0.4917   0.02309   0.02008  -0.1007   0.9669   0.0046
  -8.750  -0.4688   0.01765   0.01423  -0.1035   0.9609   0.0048
  -8.500  -0.4388   0.01589   0.01226  -0.1051   0.9566   0.0050
  -8.250  -0.4058   0.01468   0.01087  -0.1069   0.9532   0.0052
  -8.000  -0.3744   0.01368   0.00971  -0.1082   0.9475   0.0055
  -7.750  -0.3409   0.01281   0.00868  -0.1098   0.9416   0.0058
  -7.500  -0.3084   0.01211   0.00782  -0.1110   0.9350   0.0061
  -7.250  -0.2773   0.01150   0.00707  -0.1119   0.9276   0.0064
  -7.000  -0.2483   0.01081   0.00623  -0.1123   0.9203   0.0071
  -6.750  -0.2199   0.01034   0.00565  -0.1124   0.9121   0.0079
  -6.500  -0.1925   0.00996   0.00515  -0.1123   0.9047   0.0087
  -6.250  -0.1652   0.00965   0.00473  -0.1122   0.8978   0.0093
  -6.000  -0.1384   0.00925   0.00426  -0.1119   0.8908   0.0111
  -5.750  -0.1116   0.00897   0.00394  -0.1116   0.8827   0.0128
  -5.500  -0.0849   0.00871   0.00364  -0.1112   0.8742   0.0150
  -5.250  -0.0581   0.00854   0.00346  -0.1109   0.8652   0.0181
  -5.000  -0.0313   0.00844   0.00330  -0.1105   0.8538   0.0201
  -4.750  -0.0048   0.00837   0.00315  -0.1101   0.8378   0.0209
  -4.500   0.0203   0.00835   0.00299  -0.1093   0.8006   0.0212
  -4.250   0.0420   0.00827   0.00259  -0.1078   0.7412   0.0231
  -3.750   0.0918   0.00815   0.00217  -0.1062   0.6878   0.0264
  -3.500   0.1179   0.00808   0.00200  -0.1057   0.6708   0.0278
  -3.250   0.1442   0.00802   0.00184  -0.1053   0.6550   0.0294
  -3.000   0.1706   0.00796   0.00169  -0.1048   0.6394   0.0305
  -2.750   0.1971   0.00792   0.00155  -0.1044   0.6248   0.0313
  -2.500   0.2238   0.00788   0.00143  -0.1040   0.6111   0.0327
  -2.250   0.2503   0.00783   0.00132  -0.1036   0.5971   0.0368
  -2.000   0.2765   0.00779   0.00124  -0.1031   0.5799   0.0417
  -1.750   0.3026   0.00776   0.00122  -0.1027   0.5630   0.0624
  -1.500   0.3293   0.00779   0.00118  -0.1023   0.5491   0.0649
  -1.250   0.3560   0.00779   0.00114  -0.1020   0.5367   0.0684
  -1.000   0.3826   0.00781   0.00111  -0.1016   0.5224   0.0712
  -0.750   0.4092   0.00786   0.00109  -0.1012   0.5078   0.0734
  -0.500   0.4358   0.00791   0.00107  -0.1009   0.4938   0.0748
  -0.250   0.4624   0.00796   0.00106  -0.1005   0.4796   0.0758
   0.000   0.4890   0.00801   0.00106  -0.1002   0.4665   0.0778
   0.250   0.5156   0.00803   0.00105  -0.0998   0.4560   0.0823
   0.500   0.5425   0.00804   0.00105  -0.0995   0.4473   0.0864
   0.750   0.5693   0.00807   0.00107  -0.0992   0.4393   0.0884
   1.250   0.6225   0.00814   0.00115  -0.0986   0.4177   0.1133
   1.500   0.6489   0.00821   0.00121  -0.0982   0.4045   0.1272
   1.750   0.6754   0.00829   0.00127  -0.0979   0.3933   0.1347
   2.000   0.7019   0.00838   0.00134  -0.0976   0.3826   0.1391
   2.250   0.7283   0.00847   0.00141  -0.0972   0.3710   0.1436
   2.500   0.7546   0.00857   0.00149  -0.0969   0.3580   0.1475
   2.750   0.7806   0.00870   0.00158  -0.0965   0.3427   0.1509
   3.000   0.8062   0.00888   0.00170  -0.0960   0.3221   0.1534
   3.250   0.8318   0.00905   0.00182  -0.0956   0.3032   0.1569
   3.500   0.8571   0.00925   0.00196  -0.0951   0.2841   0.1619
   3.750   0.8823   0.00945   0.00212  -0.0946   0.2656   0.1665
   4.000   0.9064   0.00977   0.00232  -0.0939   0.2381   0.1727
   4.250   0.9296   0.01017   0.00258  -0.0932   0.2025   0.1819
   4.500   0.9536   0.01046   0.00282  -0.0925   0.1767   0.2110
   4.750   0.9726   0.01123   0.00333  -0.0911   0.1061   0.2615
   5.000   0.9961   0.01152   0.00364  -0.0904   0.0890   0.3141
   5.500   1.0495   0.01100   0.00434  -0.0907   0.0616   1.0000
   5.750   1.0690   0.01178   0.00491  -0.0893   0.0174   1.0000
   6.000   1.0933   0.01204   0.00520  -0.0886   0.0130   1.0000
   6.250   1.1172   0.01235   0.00552  -0.0879   0.0111   1.0000
   6.500   1.1404   0.01272   0.00591  -0.0871   0.0093   1.0000
   6.750   1.1639   0.01305   0.00628  -0.0863   0.0083   1.0000
   7.000   1.1872   0.01337   0.00663  -0.0855   0.0075   1.0000
   7.250   1.2100   0.01374   0.00701  -0.0847   0.0068   1.0000
   7.500   1.2318   0.01419   0.00748  -0.0837   0.0061   1.0000
   7.750   1.2534   0.01466   0.00800  -0.0826   0.0056   1.0000
   8.000   1.2752   0.01507   0.00845  -0.0816   0.0053   1.0000
   8.250   1.2966   0.01551   0.00895  -0.0806   0.0049   1.0000
   8.500   1.3176   0.01596   0.00942  -0.0795   0.0046   1.0000
   8.750   1.3383   0.01641   0.00990  -0.0784   0.0042   1.0000
   9.000   1.3571   0.01700   0.01053  -0.0770   0.0039   1.0000
   9.250   1.3744   0.01769   0.01129  -0.0753   0.0037   1.0000
   9.500   1.3924   0.01828   0.01195  -0.0738   0.0036   1.0000
   9.750   1.4096   0.01889   0.01262  -0.0721   0.0034   1.0000
  10.000   1.4253   0.01956   0.01336  -0.0703   0.0033   1.0000
  10.250   1.4396   0.02021   0.01408  -0.0682   0.0031   1.0000
  10.500   1.4506   0.02092   0.01488  -0.0655   0.0030   1.0000
  10.750   1.4605   0.02168   0.01571  -0.0627   0.0029   1.0000
  11.000   1.4697   0.02249   0.01658  -0.0600   0.0028   1.0000
  11.250   1.4787   0.02332   0.01749  -0.0574   0.0027   1.0000
  11.500   1.4867   0.02425   0.01848  -0.0548   0.0027   1.0000
  11.750   1.4937   0.02527   0.01958  -0.0523   0.0026   1.0000
  12.000   1.4971   0.02658   0.02097  -0.0496   0.0024   1.0000
  12.250   1.4976   0.02818   0.02267  -0.0468   0.0024   1.0000
  12.500   1.4914   0.03042   0.02504  -0.0439   0.0023   1.0000
  12.750   1.4902   0.03245   0.02719  -0.0418   0.0023   1.0000
  13.000   1.4948   0.03412   0.02895  -0.0404   0.0022   1.0000
  13.250   1.4917   0.03667   0.03163  -0.0390   0.0022   1.0000
  13.500   1.4938   0.03890   0.03395  -0.0383   0.0022   1.0000
  13.750   1.4879   0.04220   0.03739  -0.0378   0.0022   1.0000
  14.000   1.4867   0.04519   0.04050  -0.0377   0.0021   1.0000
  14.250   1.4809   0.04889   0.04433  -0.0380   0.0021   1.0000
  14.500   1.4771   0.05248   0.04806  -0.0385   0.0020   1.0000
  14.750   1.4658   0.05724   0.05296  -0.0394   0.0020   1.0000
  15.000   1.4681   0.06027   0.05607  -0.0401   0.0019   1.0000
  15.250   1.4591   0.06497   0.06089  -0.0414   0.0019   1.0000
  15.500   1.4469   0.07033   0.06639  -0.0430   0.0019   1.0000
  15.750   1.4397   0.07508   0.07126  -0.0446   0.0019   1.0000
  16.000   1.4285   0.08062   0.07692  -0.0466   0.0018   1.0000
  16.250   1.4162   0.08653   0.08296  -0.0489   0.0019   1.0000
  16.500   1.4061   0.09226   0.08881  -0.0513   0.0018   1.0000
  16.750   1.3941   0.09848   0.09515  -0.0540   0.0018   1.0000
  17.000   1.3818   0.10496   0.10176  -0.0569   0.0018   1.0000
  17.250   1.3711   0.11129   0.10821  -0.0599   0.0018   1.0000
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