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GOE 155 (SSW D.1) AIRFOIL (goe155-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 155 (SSW D.1) AIRFOIL (goe155-il)
Reynolds number: 500,000
Max Cl/Cd: 98.61 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe155-il-500000-n5.txt
Download as CSV file: xf-goe155-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 155 (SSW D.1) AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3446   0.10616   0.10397  -0.0143   0.9368   0.0078
  -8.750  -0.3398   0.10298   0.10077  -0.0153   0.9250   0.0078
  -8.500  -0.3349   0.09975   0.09752  -0.0165   0.9140   0.0078
  -8.250  -0.3300   0.09649   0.09424  -0.0177   0.9029   0.0078
  -7.750  -0.3194   0.08977   0.08746  -0.0210   0.8797   0.0081
  -7.500  -0.3139   0.08627   0.08394  -0.0233   0.8686   0.0082
  -7.250  -0.3044   0.08107   0.07870  -0.0285   0.8585   0.0088
  -7.000  -0.2895   0.07890   0.07650  -0.0307   0.8491   0.0091
  -6.750  -0.2732   0.07608   0.07363  -0.0339   0.8401   0.0095
  -6.500  -0.2557   0.07223   0.06972  -0.0384   0.8317   0.0097
  -6.250  -0.2355   0.06811   0.06554  -0.0436   0.8229   0.0100
  -6.000  -0.2129   0.06377   0.06112  -0.0491   0.8146   0.0104
  -5.750  -0.1869   0.05871   0.05596  -0.0555   0.8058   0.0110
  -5.500  -0.1566   0.05301   0.05014  -0.0629   0.7977   0.0121
  -5.250  -0.1316   0.05098   0.04802  -0.0654   0.7893   0.0127
  -5.000  -0.1020   0.04723   0.04415  -0.0699   0.7818   0.0133
  -4.750  -0.0579   0.03761   0.03415  -0.0795   0.7756   0.0156
  -4.500  -0.0325   0.03658   0.03305  -0.0806   0.7683   0.0161
  -4.250  -0.0055   0.03500   0.03134  -0.0820   0.7605   0.0167
  -4.000   0.0253   0.03187   0.02801  -0.0843   0.7534   0.0177
  -3.750   0.0650   0.02281   0.01824  -0.0881   0.7478   0.0207
  -3.500   0.0922   0.02182   0.01710  -0.0887   0.7419   0.0212
  -3.250   0.1203   0.02053   0.01566  -0.0893   0.7362   0.0218
  -3.000   0.1489   0.01904   0.01392  -0.0898   0.7307   0.0229
  -2.750   0.1784   0.01695   0.01146  -0.0902   0.7260   0.0241
  -2.500   0.2077   0.01538   0.00956  -0.0905   0.7207   0.0247
  -2.250   0.2365   0.01434   0.00824  -0.0907   0.7146   0.0251
  -2.000   0.2651   0.01369   0.00737  -0.0908   0.7072   0.0257
  -1.750   0.2936   0.01333   0.00683  -0.0908   0.6990   0.0262
  -1.500   0.3223   0.01271   0.00605  -0.0910   0.6914   0.0263
  -1.250   0.3507   0.01215   0.00532  -0.0910   0.6837   0.0265
  -1.000   0.3792   0.01122   0.00426  -0.0912   0.6754   0.0270
  -0.750   0.4073   0.01070   0.00365  -0.0913   0.6669   0.0275
  -0.500   0.4356   0.01035   0.00325  -0.0914   0.6560   0.0281
  -0.250   0.4637   0.01009   0.00292  -0.0914   0.6423   0.0285
   0.000   0.4918   0.00989   0.00266  -0.0915   0.6265   0.0289
   0.250   0.5198   0.00973   0.00245  -0.0915   0.6101   0.0294
   0.500   0.5479   0.00963   0.00229  -0.0916   0.5941   0.0303
   0.750   0.5759   0.00955   0.00214  -0.0917   0.5758   0.0307
   1.000   0.6038   0.00952   0.00202  -0.0917   0.5544   0.0308
   1.250   0.6315   0.00955   0.00195  -0.0917   0.5316   0.0309
   1.500   0.6591   0.00962   0.00192  -0.0918   0.5072   0.0312
   1.750   0.6866   0.00973   0.00192  -0.0918   0.4839   0.0316
   2.000   0.7140   0.00986   0.00195  -0.0918   0.4629   0.0322
   2.250   0.7415   0.00999   0.00199  -0.0919   0.4458   0.0331
   2.500   0.7690   0.01011   0.00205  -0.0919   0.4318   0.0341
   2.750   0.7966   0.01022   0.00213  -0.0920   0.4194   0.0363
   3.000   0.8240   0.01034   0.00223  -0.0920   0.4079   0.0404
   3.250   0.8514   0.01044   0.00237  -0.0920   0.3966   0.0724
   3.750   0.9056   0.01066   0.00273  -0.0922   0.3673   0.1774
   4.250   0.9555   0.00969   0.00320  -0.0916   0.3270   1.0000
   4.500   0.9819   0.00996   0.00340  -0.0916   0.3092   1.0000
   4.750   1.0080   0.01028   0.00362  -0.0914   0.2887   1.0000
   5.000   1.0337   0.01063   0.00388  -0.0913   0.2690   1.0000
   5.250   1.0594   0.01097   0.00416  -0.0911   0.2535   1.0000
   5.500   1.0848   0.01133   0.00445  -0.0909   0.2379   1.0000
   5.750   1.1101   0.01170   0.00475  -0.0907   0.2233   1.0000
   6.000   1.1349   0.01211   0.00509  -0.0905   0.2064   1.0000
   6.250   1.1599   0.01248   0.00543  -0.0902   0.1897   1.0000
   6.500   1.1798   0.01351   0.00604  -0.0895   0.1155   1.0000
   6.750   1.1954   0.01508   0.00719  -0.0881   0.0371   1.0000
   7.000   1.2184   0.01563   0.00773  -0.0876   0.0294   1.0000
   7.250   1.2420   0.01607   0.00824  -0.0871   0.0247   1.0000
   7.500   1.2645   0.01662   0.00881  -0.0864   0.0199   1.0000
   7.750   1.2869   0.01716   0.00940  -0.0858   0.0169   1.0000
   8.000   1.3088   0.01771   0.00997  -0.0851   0.0144   1.0000
   8.250   1.3288   0.01846   0.01076  -0.0841   0.0121   1.0000
   8.500   1.3492   0.01910   0.01149  -0.0832   0.0113   1.0000
   8.750   1.3689   0.01977   0.01224  -0.0822   0.0103   1.0000
   9.000   1.3877   0.02047   0.01300  -0.0812   0.0095   1.0000
   9.250   1.4045   0.02129   0.01386  -0.0798   0.0086   1.0000
   9.500   1.4183   0.02231   0.01498  -0.0781   0.0079   1.0000
   9.750   1.4323   0.02319   0.01596  -0.0764   0.0075   1.0000
  10.000   1.4421   0.02416   0.01704  -0.0740   0.0072   1.0000
  10.250   1.4505   0.02525   0.01824  -0.0716   0.0069   1.0000
  10.500   1.4586   0.02645   0.01953  -0.0695   0.0066   1.0000
  10.750   1.4660   0.02777   0.02094  -0.0675   0.0063   1.0000
  11.000   1.4725   0.02924   0.02250  -0.0657   0.0061   1.0000
  11.250   1.4769   0.03096   0.02431  -0.0639   0.0059   1.0000
  11.500   1.4774   0.03313   0.02658  -0.0621   0.0056   1.0000
  11.750   1.4756   0.03564   0.02922  -0.0604   0.0054   1.0000
  12.000   1.4797   0.03769   0.03141  -0.0592   0.0053   1.0000
  12.250   1.4827   0.03993   0.03378  -0.0581   0.0051   1.0000
  12.500   1.4844   0.04235   0.03633  -0.0572   0.0049   1.0000
  12.750   1.4850   0.04498   0.03909  -0.0564   0.0048   1.0000
  13.000   1.4846   0.04778   0.04201  -0.0557   0.0046   1.0000
  13.250   1.4827   0.05082   0.04518  -0.0552   0.0045   1.0000
  13.500   1.4804   0.05400   0.04848  -0.0548   0.0044   1.0000
  13.750   1.4773   0.05734   0.05195  -0.0545   0.0043   1.0000
  14.000   1.4737   0.06087   0.05560  -0.0545   0.0042   1.0000
  14.250   1.4700   0.06455   0.05941  -0.0547   0.0042   1.0000
  14.500   1.4659   0.06841   0.06339  -0.0551   0.0041   1.0000
  14.750   1.4612   0.07246   0.06758  -0.0557   0.0040   1.0000
  15.000   1.4559   0.07674   0.07198  -0.0565   0.0040   1.0000
  15.250   1.4504   0.08118   0.07654  -0.0576   0.0039   1.0000
  15.500   1.4437   0.08586   0.08135  -0.0587   0.0038   1.0000
  15.750   1.4361   0.09077   0.08638  -0.0600   0.0038   1.0000
  16.000   1.4279   0.09587   0.09161  -0.0615   0.0037   1.0000
  16.250   1.4184   0.10126   0.09714  -0.0632   0.0037   1.0000
  16.500   1.4079   0.10687   0.10289  -0.0651   0.0037   1.0000
  16.750   1.3964   0.11278   0.10894  -0.0671   0.0036   1.0000
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