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GOE 54 AIRFOIL (goe54-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 54 AIRFOIL (goe54-il)
Reynolds number: 100,000
Max Cl/Cd: 44.19 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe54-il-100000-n5.txt
Download as CSV file: xf-goe54-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 54 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5331   0.11156   0.10679   0.0346   1.0000   0.0348
  -8.250  -0.5293   0.10868   0.10396   0.0310   1.0000   0.0350
  -8.000  -0.5248   0.10569   0.10101   0.0265   1.0000   0.0352
  -7.750  -0.5140   0.10206   0.09739   0.0195   1.0000   0.0353
  -7.500  -0.5055   0.09743   0.09283   0.0217   1.0000   0.0356
  -7.250  -0.4960   0.09344   0.08886   0.0222   1.0000   0.0361
  -7.000  -0.4848   0.08972   0.08516   0.0204   1.0000   0.0369
  -6.750  -0.4718   0.08603   0.08149   0.0174   1.0000   0.0380
  -6.500  -0.4559   0.08220   0.07766   0.0131   1.0000   0.0396
  -6.250  -0.4330   0.07813   0.07352   0.0057   1.0000   0.0412
  -6.000  -0.4015   0.07399   0.06917  -0.0040   1.0000   0.0418
  -5.750  -0.3854   0.06971   0.06493  -0.0053   1.0000   0.0421
  -5.500  -0.3715   0.06597   0.06125  -0.0052   1.0000   0.0428
  -5.250  -0.3516   0.06247   0.05772  -0.0072   1.0000   0.0441
  -5.000  -0.3264   0.05899   0.05416  -0.0104   1.0000   0.0466
  -4.750  -0.2876   0.05549   0.05028  -0.0167   1.0000   0.0489
  -4.500  -0.2699   0.05186   0.04674  -0.0171   1.0000   0.0498
  -4.250  -0.2456   0.04881   0.04366  -0.0186   1.0000   0.0516
  -4.000  -0.2074   0.04658   0.04097  -0.0221   1.0000   0.0556
  -3.750  -0.1843   0.04302   0.03747  -0.0233   1.0000   0.0568
  -3.500  -0.1406   0.04111   0.03498  -0.0271   0.8089   0.0640
  -3.250  -0.1249   0.03851   0.03197  -0.0258   0.6807   0.0661
  -3.000  -0.0943   0.03735   0.03014  -0.0264   0.6220   0.0738
  -2.750  -0.0715   0.03484   0.02750  -0.0267   0.5803   0.0772
  -2.500  -0.0431   0.03321   0.02548  -0.0274   0.5508   0.0873
  -2.250  -0.0155   0.03161   0.02358  -0.0281   0.5279   0.1001
  -2.000   0.0113   0.03001   0.02176  -0.0286   0.5091   0.1158
  -1.750   0.0372   0.02844   0.02004  -0.0293   0.4928   0.1447
  -1.500   0.0632   0.02693   0.01840  -0.0298   0.4785   0.1760
  -1.250   0.0916   0.02563   0.01690  -0.0301   0.4653   0.1952
  -0.750   0.1636   0.02463   0.01470  -0.0285   0.4412   0.1084
  -0.500   0.1952   0.02341   0.01321  -0.0278   0.4288   0.0798
  -0.250   0.2254   0.02268   0.01217  -0.0272   0.4165   0.0687
   0.000   0.2545   0.02202   0.01127  -0.0269   0.4049   0.0667
   0.250   0.2839   0.02176   0.01073  -0.0263   0.3930   0.0630
   0.500   0.3124   0.02094   0.00986  -0.0261   0.3814   0.0606
   0.750   0.3409   0.02046   0.00924  -0.0257   0.3708   0.0581
   1.000   0.3696   0.02033   0.00888  -0.0252   0.3602   0.0560
   1.250   0.3977   0.01988   0.00841  -0.0249   0.3491   0.0553
   1.500   0.4255   0.01949   0.00799  -0.0246   0.3397   0.0549
   1.750   0.4533   0.01930   0.00773  -0.0243   0.3305   0.0559
   2.000   0.4802   0.01882   0.00738  -0.0240   0.3227   0.0580
   2.250   0.5074   0.01864   0.00718  -0.0236   0.3151   0.0587
   2.500   0.5349   0.01856   0.00704  -0.0233   0.3072   0.0588
   2.750   0.5629   0.01852   0.00689  -0.0231   0.2988   0.0593
   3.000   0.5911   0.01856   0.00686  -0.0230   0.2902   0.0601
   3.250   0.6189   0.01863   0.00680  -0.0228   0.2826   0.0612
   3.500   0.6470   0.01876   0.00688  -0.0227   0.2754   0.0648
   3.750   0.6749   0.01892   0.00699  -0.0226   0.2691   0.0694
   4.000   0.7025   0.01918   0.00714  -0.0224   0.2640   0.0725
   4.250   0.7305   0.01944   0.00748  -0.0223   0.2582   0.0786
   4.750   0.7808   0.01841   0.00809  -0.0211   0.2488   1.0000
   5.000   0.8082   0.01886   0.00857  -0.0209   0.2436   1.0000
   5.250   0.8353   0.01931   0.00903  -0.0208   0.2382   1.0000
   5.500   0.8620   0.01977   0.00940  -0.0205   0.2334   1.0000
   5.750   0.8889   0.02030   0.00996  -0.0204   0.2282   1.0000
   6.000   0.9156   0.02081   0.01054  -0.0202   0.2225   1.0000
   6.250   0.9421   0.02132   0.01105  -0.0200   0.2178   1.0000
   6.500   0.9683   0.02194   0.01166  -0.0198   0.2139   1.0000
   6.750   0.9947   0.02260   0.01252  -0.0197   0.2089   1.0000
   7.000   1.0207   0.02325   0.01328  -0.0195   0.2044   1.0000
   7.250   1.0466   0.02388   0.01393  -0.0193   0.2008   1.0000
   7.500   1.0722   0.02465   0.01477  -0.0191   0.1974   1.0000
   7.750   1.0975   0.02553   0.01595  -0.0190   0.1929   1.0000
   8.000   1.1227   0.02612   0.01666  -0.0187   0.1879   1.0000
   8.250   1.1480   0.02647   0.01694  -0.0184   0.1834   1.0000
   8.500   1.1723   0.02717   0.01801  -0.0183   0.1763   1.0000
   8.750   1.1972   0.02745   0.01837  -0.0180   0.1709   1.0000
   9.000   1.2211   0.02813   0.01928  -0.0178   0.1651   1.0000
   9.250   1.2451   0.02863   0.01996  -0.0176   0.1592   1.0000
   9.500   1.2689   0.02913   0.02058  -0.0173   0.1544   1.0000
   9.750   1.2916   0.02996   0.02172  -0.0171   0.1480   1.0000
  10.000   1.3148   0.03030   0.02210  -0.0168   0.1427   1.0000
  10.250   1.3360   0.03140   0.02353  -0.0166   0.1359   1.0000
  10.500   1.3575   0.03199   0.02421  -0.0163   0.1298   1.0000
  10.750   1.3765   0.03326   0.02579  -0.0161   0.1219   1.0000
  11.000   1.3949   0.03422   0.02677  -0.0158   0.1146   1.0000
  11.250   1.4102   0.03595   0.02885  -0.0157   0.1059   1.0000
  11.500   1.4231   0.03772   0.03079  -0.0155   0.0986   1.0000
  11.750   1.4328   0.03990   0.03321  -0.0155   0.0909   1.0000
  12.000   1.4377   0.04258   0.03612  -0.0157   0.0845   1.0000
  12.250   1.4364   0.04585   0.03957  -0.0166   0.0797   1.0000
  12.500   1.4218   0.05086   0.04471  -0.0195   0.0777   1.0000
  12.750   1.3987   0.05929   0.05339  -0.0268   0.0768   1.0000
  13.000   1.3713   0.06809   0.06235  -0.0327   0.0762   1.0000
  13.250   1.3413   0.07698   0.07138  -0.0379   0.0757   1.0000
  13.500   1.3090   0.08631   0.08083  -0.0430   0.0752   1.0000
  13.750   1.2727   0.09662   0.09126  -0.0483   0.0746   1.0000
  14.000   1.2200   0.11070   0.10542  -0.0556   0.0743   1.0000
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