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GOE 490 AIRFOIL (goe490-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 490 AIRFOIL (goe490-il)
Reynolds number: 1,000,000
Max Cl/Cd: 114.12 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe490-il-1000000.txt
Download as CSV file: xf-goe490-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 490 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.3031   0.12922   0.12762  -0.0252   1.0000   0.0131
 -12.250  -0.3070   0.12482   0.12322  -0.0269   1.0000   0.0140
 -10.500  -0.8134   0.02716   0.02455  -0.0623   0.9976   0.0100
 -10.250  -0.7887   0.02392   0.02095  -0.0645   0.9955   0.0103
 -10.000  -0.7594   0.02229   0.01910  -0.0662   0.9942   0.0106
  -9.750  -0.7370   0.01999   0.01647  -0.0667   0.9913   0.0109
  -9.500  -0.7111   0.01823   0.01449  -0.0676   0.9888   0.0117
  -9.250  -0.6795   0.01768   0.01388  -0.0687   0.9872   0.0122
  -9.000  -0.6474   0.01712   0.01324  -0.0699   0.9859   0.0128
  -8.750  -0.6152   0.01648   0.01250  -0.0712   0.9848   0.0134
  -8.500  -0.5821   0.01593   0.01183  -0.0725   0.9839   0.0140
  -8.250  -0.5591   0.01481   0.01053  -0.0719   0.9796   0.0147
  -8.000  -0.5278   0.01459   0.01032  -0.0727   0.9772   0.0156
  -7.750  -0.4950   0.01439   0.01011  -0.0738   0.9754   0.0164
  -7.500  -0.4609   0.01413   0.00980  -0.0751   0.9739   0.0173
  -7.250  -0.4254   0.01391   0.00952  -0.0767   0.9726   0.0182
  -7.000  -0.3923   0.01284   0.00830  -0.0781   0.9713   0.0194
  -6.750  -0.3678   0.01256   0.00802  -0.0774   0.9649   0.0203
  -6.500  -0.3348   0.01239   0.00784  -0.0784   0.9622   0.0213
  -6.250  -0.3005   0.01216   0.00757  -0.0798   0.9600   0.0226
  -6.000  -0.2646   0.01192   0.00728  -0.0814   0.9582   0.0236
  -5.750  -0.2367   0.01184   0.00715  -0.0812   0.9511   0.0240
  -5.500  -0.2057   0.01044   0.00561  -0.0822   0.9461   0.0261
  -5.250  -0.1728   0.01012   0.00527  -0.0833   0.9395   0.0273
  -5.000  -0.1382   0.00979   0.00489  -0.0847   0.9321   0.0286
  -4.750  -0.1055   0.00949   0.00452  -0.0856   0.9225   0.0298
  -4.500  -0.0728   0.00929   0.00426  -0.0866   0.9124   0.0308
  -4.250  -0.0426   0.00911   0.00399  -0.0869   0.9015   0.0312
  -4.000  -0.0173   0.00847   0.00323  -0.0863   0.8895   0.0327
  -3.750   0.0088   0.00813   0.00281  -0.0858   0.8776   0.0341
  -3.500   0.0350   0.00791   0.00253  -0.0852   0.8650   0.0355
  -3.250   0.0610   0.00774   0.00228  -0.0847   0.8521   0.0366
  -3.000   0.0868   0.00760   0.00207  -0.0840   0.8386   0.0380
  -2.750   0.1125   0.00749   0.00190  -0.0834   0.8252   0.0394
  -2.500   0.1381   0.00742   0.00174  -0.0827   0.8108   0.0404
  -2.250   0.1632   0.00728   0.00153  -0.0819   0.7956   0.0437
  -2.000   0.1882   0.00716   0.00139  -0.0811   0.7802   0.0498
  -1.750   0.2122   0.00694   0.00128  -0.0802   0.7650   0.0928
  -1.500   0.2372   0.00689   0.00125  -0.0794   0.7488   0.1154
  -1.250   0.2620   0.00690   0.00121  -0.0787   0.7297   0.1270
  -0.750   0.3115   0.00696   0.00115  -0.0770   0.6890   0.1456
  -0.500   0.3364   0.00697   0.00111  -0.0763   0.6704   0.1555
  -0.250   0.3611   0.00699   0.00109  -0.0755   0.6513   0.1680
   0.000   0.3857   0.00699   0.00108  -0.0747   0.6323   0.1877
   0.250   0.4101   0.00696   0.00111  -0.0739   0.6118   0.2296
   0.500   0.4346   0.00702   0.00115  -0.0731   0.5898   0.2602
   0.750   0.4595   0.00708   0.00118  -0.0724   0.5668   0.2843
   1.000   0.4836   0.00717   0.00122  -0.0716   0.5393   0.3035
   1.250   0.5077   0.00728   0.00125  -0.0707   0.5107   0.3188
   1.500   0.5315   0.00738   0.00130  -0.0699   0.4845   0.3401
   1.750   0.5429   0.00654   0.00139  -0.0667   0.4651   0.7190
   2.000   0.6190   0.00637   0.00173  -0.0774   0.4391   0.9839
   2.250   0.6668   0.00658   0.00184  -0.0818   0.4230   0.9924
   2.500   0.7109   0.00674   0.00193  -0.0855   0.4096   0.9969
   2.750   0.7546   0.00688   0.00199  -0.0891   0.3969   1.0000
   3.000   0.7783   0.00698   0.00206  -0.0882   0.3875   1.0000
   3.250   0.8015   0.00710   0.00214  -0.0871   0.3755   1.0000
   3.500   0.8245   0.00724   0.00223  -0.0861   0.3631   1.0000
   3.750   0.8468   0.00742   0.00232  -0.0849   0.3436   1.0000
   4.000   0.8682   0.00765   0.00243  -0.0836   0.3177   1.0000
   4.250   0.8895   0.00789   0.00257  -0.0822   0.2950   1.0000
   4.500   0.9095   0.00821   0.00274  -0.0807   0.2651   1.0000
   4.750   0.9298   0.00852   0.00293  -0.0792   0.2408   1.0000
   5.000   0.9505   0.00880   0.00313  -0.0778   0.2221   1.0000
   5.250   0.9713   0.00908   0.00333  -0.0764   0.2044   1.0000
   5.500   0.9915   0.00940   0.00355  -0.0749   0.1841   1.0000
   5.750   1.0104   0.00981   0.00381  -0.0731   0.1564   1.0000
   6.000   1.0288   0.01026   0.00410  -0.0714   0.1305   1.0000
   6.250   1.0464   0.01076   0.00445  -0.0695   0.1045   1.0000
   6.500   1.0562   0.01182   0.00514  -0.0662   0.0412   1.0000
   6.750   1.0711   0.01254   0.00572  -0.0637   0.0162   1.0000
   7.000   1.0918   0.01285   0.00607  -0.0623   0.0147   1.0000
   7.250   1.1117   0.01321   0.00648  -0.0608   0.0136   1.0000
   7.500   1.1309   0.01362   0.00694  -0.0591   0.0127   1.0000
   7.750   1.1484   0.01416   0.00753  -0.0572   0.0117   1.0000
   8.000   1.1649   0.01476   0.00822  -0.0551   0.0111   1.0000
   8.250   1.1836   0.01518   0.00868  -0.0534   0.0108   1.0000
   8.500   1.2016   0.01563   0.00918  -0.0517   0.0104   1.0000
   8.750   1.2185   0.01614   0.00974  -0.0498   0.0099   1.0000
   9.000   1.2350   0.01665   0.01029  -0.0478   0.0094   1.0000
   9.250   1.2492   0.01728   0.01096  -0.0455   0.0088   1.0000
   9.500   1.2609   0.01792   0.01166  -0.0427   0.0087   1.0000
   9.750   1.2635   0.01892   0.01275  -0.0384   0.0083   1.0000
  10.000   1.2593   0.02033   0.01428  -0.0332   0.0080   1.0000
  10.250   1.2710   0.02099   0.01499  -0.0308   0.0079   1.0000
  10.500   1.2799   0.02183   0.01591  -0.0280   0.0078   1.0000
  10.750   1.2893   0.02268   0.01682  -0.0256   0.0076   1.0000
  11.000   1.2967   0.02369   0.01790  -0.0230   0.0075   1.0000
  11.250   1.3040   0.02476   0.01905  -0.0206   0.0073   1.0000
  11.500   1.3097   0.02600   0.02037  -0.0183   0.0072   1.0000
  11.750   1.3135   0.02746   0.02190  -0.0160   0.0070   1.0000
  12.000   1.3185   0.02892   0.02344  -0.0141   0.0069   1.0000
  12.250   1.3231   0.03049   0.02509  -0.0124   0.0067   1.0000
  12.500   1.3287   0.03205   0.02673  -0.0110   0.0064   1.0000
  12.750   1.3323   0.03389   0.02864  -0.0098   0.0062   1.0000
  13.000   1.3352   0.03589   0.03072  -0.0087   0.0062   1.0000
  13.250   1.3353   0.03825   0.03316  -0.0078   0.0061   1.0000
  13.500   1.3371   0.04055   0.03552  -0.0073   0.0060   1.0000
  13.750   1.3339   0.04343   0.03847  -0.0067   0.0058   1.0000
  14.000   1.3257   0.04691   0.04203  -0.0056   0.0057   1.0000
  14.250   1.3166   0.05053   0.04576  -0.0040   0.0055   1.0000
  14.500   1.3162   0.05346   0.04881  -0.0045   0.0055   1.0000
  14.750   1.3143   0.05648   0.05192  -0.0041   0.0055   1.0000
  15.000   1.3120   0.05984   0.05540  -0.0049   0.0055   1.0000
  15.250   1.3083   0.06338   0.05905  -0.0055   0.0054   1.0000
  15.500   1.3046   0.06725   0.06305  -0.0068   0.0054   1.0000
  15.750   1.2982   0.07140   0.06733  -0.0078   0.0053   1.0000
  16.000   1.2919   0.07563   0.07168  -0.0089   0.0053   1.0000
  16.250   1.2829   0.08039   0.07658  -0.0102   0.0053   1.0000
  16.500   1.2755   0.08494   0.08123  -0.0116   0.0053   1.0000
  16.750   1.2671   0.09013   0.08656  -0.0141   0.0052   1.0000
  17.000   1.2573   0.09515   0.09168  -0.0157   0.0053   1.0000
  17.250   1.2459   0.10079   0.09746  -0.0180   0.0053   1.0000
  17.500   1.2347   0.10670   0.10349  -0.0208   0.0052   1.0000
  17.750   1.2270   0.11218   0.10908  -0.0238   0.0051   1.0000
  18.000   1.2100   0.11902   0.11606  -0.0266   0.0052   1.0000
  18.250   1.1975   0.12557   0.12273  -0.0301   0.0052   1.0000
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