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GOE 393 AIRFOIL (goe393-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 393 AIRFOIL (goe393-il)
Reynolds number: 1,000,000
Max Cl/Cd: 120.4 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe393-il-1000000.txt
Download as CSV file: xf-goe393-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 393 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5001   0.10075   0.09923   0.0170   1.0000   0.0158
  -8.250  -0.4960   0.09676   0.09525   0.0147   1.0000   0.0158
  -8.000  -0.4949   0.09232   0.09083   0.0133   1.0000   0.0162
  -7.750  -0.4850   0.09001   0.08853   0.0122   1.0000   0.0164
  -7.500  -0.4734   0.08733   0.08586   0.0099   1.0000   0.0168
  -7.250  -0.4600   0.08431   0.08285   0.0067   1.0000   0.0173
  -7.000  -0.4452   0.08082   0.07936   0.0028   1.0000   0.0182
  -6.250  -0.3829   0.06035   0.05875  -0.0223   1.0000   0.0204
  -6.000  -0.3562   0.05815   0.05649  -0.0254   0.9479   0.0209
  -5.750  -0.3441   0.05716   0.05501  -0.0242   0.7951   0.0214
  -5.500  -0.3217   0.05508   0.05267  -0.0261   0.7407   0.0223
  -5.250  -0.2847   0.05025   0.04761  -0.0324   0.7155   0.0253
  -4.750  -0.2270   0.01620   0.01160  -0.0492   0.6982   0.0261
  -4.500  -0.2011   0.01439   0.00947  -0.0492   0.6814   0.0268
  -4.250  -0.1740   0.01373   0.00866  -0.0491   0.6666   0.0275
  -4.000  -0.1466   0.01326   0.00805  -0.0490   0.6528   0.0282
  -3.750  -0.1192   0.01252   0.00712  -0.0489   0.6402   0.0287
  -3.500  -0.0916   0.01178   0.00621  -0.0487   0.6290   0.0291
  -3.250  -0.0640   0.01115   0.00541  -0.0485   0.6191   0.0294
  -2.750  -0.0083   0.01015   0.00415  -0.0481   0.5999   0.0304
  -2.500   0.0196   0.00985   0.00376  -0.0479   0.5908   0.0311
  -2.250   0.0475   0.00956   0.00338  -0.0477   0.5819   0.0317
  -2.000   0.0755   0.00931   0.00305  -0.0475   0.5741   0.0320
  -1.750   0.1035   0.00911   0.00278  -0.0473   0.5661   0.0323
  -1.500   0.1313   0.00867   0.00226  -0.0471   0.5589   0.0329
  -1.250   0.1592   0.00837   0.00189  -0.0469   0.5512   0.0337
  -1.000   0.1873   0.00817   0.00164  -0.0468   0.5438   0.0346
  -0.750   0.2153   0.00802   0.00146  -0.0466   0.5359   0.0358
  -0.500   0.2434   0.00790   0.00131  -0.0464   0.5288   0.0375
  -0.250   0.2715   0.00781   0.00119  -0.0463   0.5213   0.0396
   0.000   0.2997   0.00774   0.00109  -0.0461   0.5144   0.0428
   0.250   0.3277   0.00761   0.00108  -0.0460   0.5068   0.0665
   0.500   0.3559   0.00764   0.00113  -0.0459   0.4996   0.0810
   0.750   0.3841   0.00771   0.00118  -0.0458   0.4917   0.0860
   1.000   0.4122   0.00771   0.00118  -0.0457   0.4836   0.0911
   1.500   0.4684   0.00777   0.00121  -0.0454   0.4618   0.0978
   1.750   0.4965   0.00782   0.00125  -0.0453   0.4526   0.1001
   2.000   0.5244   0.00781   0.00122  -0.0452   0.4426   0.1046
   2.250   0.5524   0.00783   0.00124  -0.0451   0.4301   0.1082
   2.500   0.5803   0.00789   0.00126  -0.0450   0.4152   0.1113
   2.750   0.6082   0.00797   0.00130  -0.0449   0.4015   0.1144
   3.000   0.6360   0.00800   0.00133  -0.0448   0.3883   0.1208
   3.250   0.6638   0.00807   0.00139  -0.0448   0.3760   0.1258
   3.500   0.6916   0.00814   0.00145  -0.0447   0.3659   0.1346
   3.750   0.7193   0.00818   0.00155  -0.0446   0.3563   0.1598
   4.000   0.7460   0.00660   0.00177  -0.0448   0.3481   1.0000
   4.250   0.7736   0.00676   0.00187  -0.0446   0.3394   1.0000
   4.500   0.8013   0.00687   0.00197  -0.0445   0.3318   1.0000
   4.750   0.8288   0.00702   0.00210  -0.0444   0.3231   1.0000
   5.000   0.8563   0.00717   0.00222  -0.0442   0.3135   1.0000
   5.250   0.8837   0.00734   0.00236  -0.0441   0.3011   1.0000
   5.500   0.9107   0.00758   0.00252  -0.0440   0.2807   1.0000
   5.750   0.9373   0.00790   0.00271  -0.0438   0.2470   1.0000
   6.250   0.9869   0.00938   0.00359  -0.0434   0.1316   1.0000
   6.500   1.0127   0.00983   0.00394  -0.0432   0.1094   1.0000
   6.750   1.0389   0.01020   0.00425  -0.0430   0.0964   1.0000
   7.250   1.0914   0.01085   0.00486  -0.0427   0.0792   1.0000
   7.500   1.1174   0.01120   0.00518  -0.0425   0.0688   1.0000
   7.750   1.1416   0.01188   0.00567  -0.0422   0.0418   1.0000
   8.000   1.1655   0.01262   0.00631  -0.0418   0.0266   1.0000
   8.250   1.1903   0.01315   0.00685  -0.0414   0.0217   1.0000
   8.500   1.2146   0.01376   0.00749  -0.0410   0.0184   1.0000
   8.750   1.2394   0.01421   0.00797  -0.0407   0.0169   1.0000
   9.000   1.2632   0.01483   0.00861  -0.0403   0.0152   1.0000
   9.250   1.2862   0.01556   0.00942  -0.0397   0.0140   1.0000
   9.500   1.3101   0.01608   0.01000  -0.0393   0.0134   1.0000
   9.750   1.3334   0.01667   0.01064  -0.0389   0.0126   1.0000
  10.000   1.3561   0.01732   0.01134  -0.0384   0.0120   1.0000
  10.250   1.3764   0.01827   0.01235  -0.0377   0.0112   1.0000
  10.500   1.3946   0.01946   0.01365  -0.0368   0.0105   1.0000
  10.750   1.4165   0.02006   0.01432  -0.0362   0.0102   1.0000
  11.000   1.4368   0.02083   0.01517  -0.0355   0.0098   1.0000
  11.250   1.4561   0.02168   0.01609  -0.0347   0.0094   1.0000
  11.500   1.4744   0.02257   0.01705  -0.0339   0.0091   1.0000
  11.750   1.4915   0.02353   0.01808  -0.0330   0.0088   1.0000
  12.000   1.5061   0.02467   0.01929  -0.0319   0.0085   1.0000
  12.250   1.5143   0.02634   0.02106  -0.0304   0.0081   1.0000
  12.500   1.5082   0.02881   0.02370  -0.0275   0.0079   1.0000
  12.750   1.5052   0.03117   0.02619  -0.0260   0.0078   1.0000
  13.000   1.5107   0.03316   0.02829  -0.0258   0.0077   1.0000
  13.250   1.5151   0.03562   0.03087  -0.0263   0.0076   1.0000
  13.500   1.5180   0.03847   0.03384  -0.0271   0.0075   1.0000
  13.750   1.5189   0.04167   0.03716  -0.0282   0.0074   1.0000
  14.000   1.5175   0.04518   0.04079  -0.0292   0.0073   1.0000
  14.250   1.5151   0.04880   0.04452  -0.0303   0.0072   1.0000
  14.500   1.5108   0.05269   0.04852  -0.0315   0.0071   1.0000
  14.750   1.5054   0.05672   0.05267  -0.0327   0.0070   1.0000
  15.000   1.4980   0.06107   0.05713  -0.0340   0.0069   1.0000
  15.250   1.4893   0.06562   0.06180  -0.0354   0.0068   1.0000
  15.500   1.4806   0.07027   0.06656  -0.0370   0.0067   1.0000
  15.750   1.4700   0.07524   0.07163  -0.0387   0.0067   1.0000
  16.000   1.4597   0.08041   0.07691  -0.0406   0.0066   1.0000
  16.250   1.4494   0.08581   0.08242  -0.0428   0.0065   1.0000
  16.500   1.4386   0.09141   0.08812  -0.0451   0.0065   1.0000
  16.750   1.4265   0.09735   0.09418  -0.0476   0.0064   1.0000
  17.000   1.4146   0.10337   0.10030  -0.0501   0.0064   1.0000
  17.250   1.4017   0.10965   0.10668  -0.0529   0.0064   1.0000
  17.500   1.3886   0.11612   0.11326  -0.0558   0.0063   1.0000
  17.750   1.3745   0.12292   0.12018  -0.0590   0.0063   1.0000
  18.000   1.3608   0.12974   0.12710  -0.0623   0.0063   1.0000
  18.250   1.3465   0.13690   0.13437  -0.0659   0.0062   1.0000
  18.500   1.3322   0.14428   0.14186  -0.0698   0.0062   1.0000
  18.750   1.3176   0.15198   0.14967  -0.0740   0.0062   1.0000
  19.000   1.3018   0.16024   0.15805  -0.0787   0.0062   1.0000
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