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GOE 532 AIRFOIL (goe532-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 532 AIRFOIL (goe532-il)
Reynolds number: 1,000,000
Max Cl/Cd: 115.7 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe532-il-1000000.txt
Download as CSV file: xf-goe532-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 532 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.3245   0.12279   0.12099  -0.0271   1.0000   0.0214
 -11.750  -0.3202   0.11942   0.11764  -0.0282   1.0000   0.0221
 -11.250  -0.3340   0.10730   0.10553  -0.0340   1.0000   0.0233
 -11.000  -0.3277   0.10487   0.10311  -0.0344   1.0000   0.0234
 -10.750  -0.3202   0.10273   0.10098  -0.0345   1.0000   0.0235
 -10.500  -0.3122   0.10084   0.09911  -0.0345   1.0000   0.0238
 -10.250  -0.3066   0.09850   0.09679  -0.0348   1.0000   0.0240
 -10.000  -0.3025   0.09596   0.09427  -0.0352   1.0000   0.0244
  -9.750  -0.2316   0.07455   0.07297  -0.0487   0.9852   0.0270
  -9.500  -0.2161   0.07126   0.06968  -0.0514   0.9751   0.0272
  -9.250  -0.1952   0.06731   0.06571  -0.0559   0.9649   0.0275
  -9.000  -0.3829   0.03514   0.03265  -0.1021   0.9571   0.0268
  -8.750  -0.3560   0.03104   0.02840  -0.1069   0.9414   0.0264
  -8.500  -0.3499   0.02470   0.02118  -0.1095   0.9112   0.0269
  -8.250  -0.3365   0.02133   0.01739  -0.1091   0.8899   0.0271
  -8.000  -0.3170   0.01958   0.01539  -0.1085   0.8721   0.0272
  -7.750  -0.2944   0.01863   0.01429  -0.1079   0.8563   0.0275
  -7.500  -0.2703   0.01799   0.01355  -0.1073   0.8418   0.0278
  -7.250  -0.2463   0.01727   0.01270  -0.1067   0.8278   0.0280
  -7.000  -0.2219   0.01659   0.01188  -0.1061   0.8138   0.0283
  -6.750  -0.1976   0.01583   0.01096  -0.1055   0.7988   0.0286
  -6.500  -0.1732   0.01505   0.01001  -0.1048   0.7824   0.0289
  -6.250  -0.1481   0.01446   0.00926  -0.1042   0.7638   0.0294
  -6.000  -0.1229   0.01390   0.00853  -0.1036   0.7420   0.0298
  -5.750  -0.0980   0.01336   0.00779  -0.1028   0.7151   0.0301
  -5.500  -0.0731   0.01293   0.00717  -0.1020   0.6845   0.0304
  -5.250  -0.0480   0.01260   0.00665  -0.1013   0.6564   0.0306
  -5.000  -0.0219   0.01236   0.00625  -0.1007   0.6338   0.0308
  -4.750   0.0037   0.01178   0.00555  -0.1002   0.6169   0.0311
  -4.500   0.0290   0.01114   0.00483  -0.0996   0.6017   0.0316
  -4.250   0.0553   0.01084   0.00448  -0.0991   0.5873   0.0320
  -4.000   0.0823   0.01062   0.00421  -0.0987   0.5746   0.0326
  -3.750   0.1094   0.01044   0.00398  -0.0984   0.5628   0.0332
  -3.500   0.1363   0.01027   0.00373  -0.0980   0.5503   0.0337
  -3.250   0.1635   0.01007   0.00348  -0.0976   0.5392   0.0342
  -3.000   0.1908   0.00989   0.00326  -0.0972   0.5300   0.0347
  -2.750   0.2181   0.00975   0.00306  -0.0969   0.5206   0.0352
  -2.500   0.2458   0.00965   0.00291  -0.0966   0.5123   0.0355
  -2.250   0.2726   0.00934   0.00255  -0.0962   0.5039   0.0365
  -2.000   0.3002   0.00922   0.00240  -0.0959   0.4965   0.0374
  -1.750   0.3279   0.00912   0.00228  -0.0957   0.4893   0.0385
  -1.500   0.3554   0.00909   0.00220  -0.0953   0.4816   0.0397
  -1.250   0.3835   0.00902   0.00212  -0.0951   0.4749   0.0408
  -1.000   0.4109   0.00891   0.00197  -0.0948   0.4677   0.0429
  -0.750   0.4388   0.00887   0.00191  -0.0946   0.4619   0.0451
  -0.500   0.4667   0.00880   0.00184  -0.0943   0.4562   0.0487
  -0.250   0.4942   0.00876   0.00179  -0.0940   0.4503   0.0570
   0.000   0.5204   0.00825   0.00173  -0.0938   0.4453   0.2109
   0.250   0.5470   0.00791   0.00176  -0.0936   0.4404   0.3439
   0.500   0.5739   0.00779   0.00180  -0.0933   0.4344   0.4156
   0.750   0.6009   0.00773   0.00186  -0.0929   0.4292   0.4743
   1.000   0.6282   0.00762   0.00191  -0.0927   0.4240   0.5360
   1.250   0.6549   0.00758   0.00198  -0.0923   0.4168   0.5935
   1.500   0.6810   0.00749   0.00207  -0.0917   0.4099   0.6720
   1.750   0.7061   0.00734   0.00215  -0.0909   0.4037   0.7602
   2.000   0.7480   0.00699   0.00223  -0.0937   0.3957   1.0000
   2.250   0.7756   0.00707   0.00227  -0.0934   0.3885   1.0000
   2.500   0.8024   0.00721   0.00233  -0.0930   0.3795   1.0000
   2.750   0.8297   0.00731   0.00239  -0.0928   0.3702   1.0000
   3.000   0.8564   0.00745   0.00247  -0.0924   0.3584   1.0000
   3.250   0.8828   0.00763   0.00256  -0.0920   0.3428   1.0000
   3.500   0.9078   0.00792   0.00269  -0.0914   0.3153   1.0000
   3.750   0.9282   0.00861   0.00303  -0.0901   0.2520   1.0000
   4.250   0.9743   0.00954   0.00362  -0.0884   0.1970   1.0000
   4.500   0.9998   0.00979   0.00381  -0.0878   0.1894   1.0000
   4.750   1.0251   0.01003   0.00400  -0.0873   0.1836   1.0000
   5.000   1.0505   0.01027   0.00421  -0.0868   0.1787   1.0000
   5.250   1.0765   0.01044   0.00437  -0.0864   0.1767   1.0000
   5.500   1.1024   0.01062   0.00455  -0.0859   0.1746   1.0000
   5.750   1.1279   0.01082   0.00474  -0.0855   0.1721   1.0000
   6.000   1.1530   0.01105   0.00494  -0.0849   0.1692   1.0000
   6.250   1.1776   0.01130   0.00518  -0.0843   0.1658   1.0000
   6.500   1.2022   0.01155   0.00542  -0.0837   0.1630   1.0000
   6.750   1.2279   0.01170   0.00559  -0.0833   0.1618   1.0000
   7.000   1.2532   0.01187   0.00578  -0.0828   0.1599   1.0000
   7.250   1.2780   0.01208   0.00599  -0.0823   0.1572   1.0000
   7.500   1.3019   0.01233   0.00622  -0.0816   0.1536   1.0000
   7.750   1.3249   0.01264   0.00651  -0.0808   0.1491   1.0000
   8.000   1.3500   0.01279   0.00669  -0.0803   0.1465   1.0000
   8.250   1.3740   0.01302   0.00690  -0.0797   0.1414   1.0000
   8.500   1.3963   0.01333   0.00717  -0.0788   0.1333   1.0000
   9.000   1.4269   0.01476   0.00826  -0.0750   0.0871   1.0000
   9.250   1.4436   0.01531   0.00879  -0.0733   0.0827   1.0000
   9.500   1.4615   0.01576   0.00926  -0.0717   0.0801   1.0000
   9.750   1.4784   0.01613   0.00967  -0.0699   0.0790   1.0000
  10.000   1.4930   0.01656   0.01014  -0.0678   0.0777   1.0000
  10.250   1.5066   0.01705   0.01066  -0.0655   0.0764   1.0000
  10.500   1.5187   0.01761   0.01126  -0.0631   0.0750   1.0000
  10.750   1.5300   0.01824   0.01192  -0.0607   0.0736   1.0000
  11.000   1.5389   0.01901   0.01272  -0.0582   0.0719   1.0000
  11.250   1.5480   0.01980   0.01357  -0.0558   0.0707   1.0000
  11.500   1.5619   0.02039   0.01421  -0.0541   0.0702   1.0000
  11.750   1.5743   0.02109   0.01497  -0.0524   0.0696   1.0000
  12.000   1.5857   0.02188   0.01582  -0.0507   0.0689   1.0000
  12.250   1.5960   0.02279   0.01678  -0.0490   0.0682   1.0000
  12.500   1.6059   0.02378   0.01782  -0.0475   0.0673   1.0000
  12.750   1.6150   0.02487   0.01897  -0.0460   0.0662   1.0000
  13.000   1.6225   0.02615   0.02029  -0.0445   0.0652   1.0000
  13.250   1.6273   0.02771   0.02190  -0.0431   0.0641   1.0000
  13.500   1.6275   0.02975   0.02401  -0.0417   0.0627   1.0000
  13.750   1.6290   0.03181   0.02614  -0.0406   0.0618   1.0000
  14.000   1.6406   0.03305   0.02744  -0.0400   0.0613   1.0000
  14.250   1.6500   0.03453   0.02899  -0.0395   0.0606   1.0000
  14.500   1.6579   0.03621   0.03073  -0.0390   0.0598   1.0000
  14.750   1.6647   0.03805   0.03263  -0.0386   0.0589   1.0000
  15.000   1.6699   0.04009   0.03474  -0.0383   0.0582   1.0000
  15.250   1.6739   0.04233   0.03703  -0.0381   0.0573   1.0000
  15.500   1.6753   0.04492   0.03968  -0.0380   0.0566   1.0000
  15.750   1.6742   0.04781   0.04263  -0.0380   0.0559   1.0000
  16.000   1.6693   0.05122   0.04612  -0.0382   0.0549   1.0000
  16.250   1.6611   0.05511   0.05010  -0.0385   0.0540   1.0000
  16.500   1.6660   0.05747   0.05253  -0.0387   0.0537   1.0000
  16.750   1.6695   0.06004   0.05518  -0.0390   0.0531   1.0000
  17.000   1.6704   0.06295   0.05816  -0.0394   0.0526   1.0000
  17.250   1.6720   0.06584   0.06112  -0.0399   0.0519   1.0000
  17.500   1.6724   0.06890   0.06426  -0.0405   0.0512   1.0000
  17.750   1.6723   0.07207   0.06749  -0.0411   0.0503   1.0000
  18.000   1.6703   0.07554   0.07102  -0.0420   0.0496   1.0000
  18.250   1.6665   0.07935   0.07488  -0.0430   0.0487   1.0000
  18.500   1.6584   0.08381   0.07941  -0.0443   0.0477   1.0000
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