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GOE 177 AIRFOIL (goe177-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 177 AIRFOIL (goe177-il)
Reynolds number: 50,000
Max Cl/Cd: 39.12 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe177-il-50000.txt
Download as CSV file: xf-goe177-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 177 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3454   0.11099   0.10448  -0.0132   1.0000   0.1254
  -8.000  -0.3462   0.10946   0.10305  -0.0151   1.0000   0.1300
  -7.750  -0.3553   0.10957   0.10332  -0.0182   1.0000   0.1315
  -7.500  -0.3330   0.10245   0.09618  -0.0156   1.0000   0.1382
  -7.250  -0.3337   0.10063   0.09447  -0.0167   1.0000   0.1435
  -7.000  -0.3393   0.10080   0.09478  -0.0231   1.0000   0.1459
  -6.750  -0.3229   0.09425   0.08826  -0.0180   1.0000   0.1515
  -6.500  -0.3198   0.09217   0.08626  -0.0203   1.0000   0.1580
  -6.250  -0.3165   0.08961   0.08381  -0.0231   1.0000   0.1616
  -6.000  -0.3073   0.08582   0.08007  -0.0209   1.0000   0.1687
  -5.750  -0.3040   0.08425   0.07860  -0.0263   1.0000   0.1752
  -5.500  -0.2959   0.08018   0.07461  -0.0225   1.0000   0.1824
  -5.250  -0.2896   0.07774   0.07224  -0.0256   1.0000   0.1907
  -5.000  -0.2794   0.07608   0.07059  -0.0298   1.0000   0.2030
  -4.750  -0.2755   0.07186   0.06648  -0.0243   1.0000   0.2101
  -4.500  -0.2682   0.06918   0.06386  -0.0249   1.0000   0.2220
  -4.250  -0.2616   0.06662   0.06136  -0.0246   1.0000   0.2371
  -4.000  -0.2516   0.06477   0.05952  -0.0271   1.0000   0.2604
  -3.750  -0.2501   0.06189   0.05676  -0.0235   1.0000   0.2777
  -3.500  -0.2438   0.05979   0.05471  -0.0233   1.0000   0.3040
  -2.750  -0.2319   0.05285   0.04801  -0.0170   1.0000   0.3927
  -2.000  -0.0576   0.04185   0.03519  -0.0546   1.0000   0.2165
  -1.750   0.0263   0.03545   0.02748  -0.0660   0.9928   0.1591
  -1.500   0.0955   0.03219   0.02354  -0.0743   0.9789   0.1761
  -1.250   0.1587   0.02989   0.02081  -0.0811   0.9628   0.2077
  -1.000   0.2191   0.02826   0.01876  -0.0872   0.9453   0.2490
  -0.750   0.2793   0.02713   0.01729  -0.0927   0.9278   0.2892
  -0.500   0.3311   0.02624   0.01626  -0.0967   0.9081   0.3294
  -0.250   0.3839   0.02494   0.01505  -0.1004   0.8902   0.3886
   0.000   0.4289   0.02226   0.01353  -0.1016   0.8736   1.0000
   0.250   0.4691   0.02232   0.01310  -0.1030   0.8526   1.0000
   0.500   0.5073   0.02233   0.01278  -0.1038   0.8329   1.0000
   0.750   0.5424   0.02238   0.01256  -0.1041   0.8138   1.0000
   1.000   0.5714   0.02266   0.01264  -0.1035   0.7931   1.0000
   1.250   0.6018   0.02286   0.01264  -0.1029   0.7750   1.0000
   1.500   0.6288   0.02326   0.01289  -0.1021   0.7563   1.0000
   1.750   0.6543   0.02379   0.01329  -0.1012   0.7378   1.0000
   2.000   0.6803   0.02430   0.01368  -0.1004   0.7211   1.0000
   2.250   0.7060   0.02486   0.01414  -0.0996   0.7054   1.0000
   2.500   0.7312   0.02551   0.01474  -0.0988   0.6905   1.0000
   2.750   0.7558   0.02625   0.01543  -0.0981   0.6764   1.0000
   3.000   0.7799   0.02708   0.01623  -0.0975   0.6630   1.0000
   3.250   0.8033   0.02803   0.01718  -0.0971   0.6503   1.0000
   3.500   0.8265   0.02905   0.01824  -0.0967   0.6388   1.0000
   3.750   0.8509   0.02997   0.01922  -0.0962   0.6285   1.0000
   4.000   0.8754   0.03087   0.02016  -0.0957   0.6188   1.0000
   4.250   0.8951   0.03244   0.02185  -0.0956   0.6084   1.0000
   4.500   0.9176   0.03372   0.02322  -0.0953   0.6001   1.0000
   4.750   0.9396   0.03502   0.02463  -0.0951   0.5916   1.0000
   5.000   0.9567   0.03689   0.02673  -0.0949   0.5821   1.0000
   5.250   0.9813   0.03772   0.02764  -0.0941   0.5735   1.0000
   5.500   1.0008   0.03910   0.02917  -0.0934   0.5634   1.0000
   5.750   1.0155   0.04105   0.03130  -0.0929   0.5528   1.0000
   6.000   1.0364   0.04217   0.03257  -0.0920   0.5431   1.0000
   6.250   1.0619   0.04274   0.03335  -0.0909   0.5341   1.0000
   6.500   1.0675   0.04590   0.03675  -0.0907   0.5243   1.0000
   6.750   1.0865   0.04718   0.03821  -0.0896   0.5145   1.0000
   7.000   1.1353   0.04204   0.03307  -0.0847   0.4877   1.0000
   7.250   1.1588   0.04179   0.03298  -0.0826   0.4717   1.0000
   7.500   1.1972   0.03730   0.02841  -0.0783   0.4385   1.0000
   7.750   1.2232   0.03670   0.02796  -0.0765   0.4224   1.0000
   8.000   1.2456   0.03616   0.02762  -0.0744   0.4030   1.0000
   8.250   1.2676   0.03464   0.02624  -0.0715   0.3751   1.0000
   8.500   1.2820   0.03300   0.02466  -0.0677   0.3356   1.0000
   8.750   1.2838   0.03282   0.02479  -0.0635   0.2760   1.0000
   9.000   1.2728   0.03495   0.02610  -0.0593   0.1476   1.0000
   9.250   1.2574   0.03892   0.02950  -0.0560   0.1145   1.0000
   9.500   1.2449   0.04236   0.03288  -0.0530   0.1008   1.0000
   9.750   1.2337   0.04594   0.03645  -0.0511   0.0930   1.0000
  10.000   1.2264   0.04945   0.04009  -0.0499   0.0866   1.0000
  10.250   1.2178   0.05334   0.04401  -0.0494   0.0827   1.0000
  10.500   1.2149   0.05677   0.04755  -0.0486   0.0789   1.0000
  10.750   1.2135   0.06003   0.05087  -0.0478   0.0754   1.0000
  11.000   1.2138   0.06297   0.05370  -0.0464   0.0720   1.0000
  11.250   1.2252   0.06487   0.05578  -0.0438   0.0681   1.0000
  11.500   1.2467   0.06602   0.05694  -0.0402   0.0634   1.0000
  11.750   1.3240   0.06760   0.05864  -0.0350   0.0606   1.0000
  12.000   1.3373   0.07184   0.06334  -0.0339   0.0606   1.0000
  12.250   1.3415   0.07641   0.06823  -0.0329   0.0609   1.0000
  12.500   1.3362   0.08081   0.07299  -0.0322   0.0612   1.0000
  12.750   1.3176   0.08491   0.07743  -0.0322   0.0617   1.0000
  13.000   1.2948   0.08991   0.08277  -0.0336   0.0622   1.0000
  13.250   1.2687   0.09596   0.08913  -0.0363   0.0629   1.0000
  13.500   1.2366   0.10344   0.09683  -0.0409   0.0636   1.0000
  13.750   1.2011   0.11262   0.10627  -0.0473   0.0646   1.0000
  14.000   1.1636   0.12365   0.11748  -0.0554   0.0659   1.0000
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