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SA7026 (sa7026-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: SA7026 (sa7026-il)
Reynolds number: 500,000
Max Cl/Cd: 106.44 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7026-il-500000-n5.txt
Download as CSV file: xf-sa7026-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7026                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3306   0.11356   0.11124  -0.0388   1.0000   0.0090
 -10.250  -0.3276   0.11054   0.10825  -0.0393   1.0000   0.0090
 -10.000  -0.3264   0.10725   0.10499  -0.0398   1.0000   0.0091
  -9.500  -0.3115   0.09988   0.09762  -0.0441   0.9911   0.0091
  -9.250  -0.3003   0.09553   0.09328  -0.0478   0.9870   0.0091
  -9.000  -0.2878   0.09110   0.08885  -0.0519   0.9835   0.0091
  -8.750  -0.2753   0.08679   0.08454  -0.0561   0.9789   0.0091
  -8.500  -0.2695   0.08056   0.07833  -0.0616   0.9734   0.0095
  -8.250  -0.2559   0.07651   0.07427  -0.0663   0.9680   0.0098
  -8.000  -0.2420   0.07219   0.06995  -0.0715   0.9601   0.0099
  -7.750  -0.2261   0.07008   0.06782  -0.0743   0.9526   0.0108
  -7.500  -0.2191   0.06665   0.06438  -0.0777   0.9410   0.0113
  -7.250  -0.2138   0.06293   0.06063  -0.0815   0.9299   0.0119
  -7.000  -0.2075   0.05868   0.05634  -0.0859   0.9194   0.0124
  -6.750  -0.1990   0.05365   0.05125  -0.0910   0.9105   0.0127
  -6.500  -0.1790   0.04756   0.04499  -0.0968   0.9028   0.0143
  -6.000  -0.1627   0.03335   0.03022  -0.1022   0.8882   0.0087
  -5.750  -0.1473   0.02821   0.02470  -0.1033   0.8817   0.0082
  -5.500  -0.1284   0.02400   0.02004  -0.1035   0.8765   0.0079
  -5.250  -0.1070   0.02055   0.01612  -0.1033   0.8715   0.0076
  -5.000  -0.0835   0.01796   0.01310  -0.1029   0.8662   0.0075
  -4.750  -0.0587   0.01605   0.01082  -0.1025   0.8616   0.0075
  -4.500  -0.0330   0.01460   0.00906  -0.1021   0.8561   0.0075
  -4.250  -0.0069   0.01346   0.00768  -0.1017   0.8506   0.0077
  -4.000   0.0196   0.01254   0.00658  -0.1014   0.8458   0.0080
  -3.750   0.0463   0.01182   0.00573  -0.1011   0.8401   0.0084
  -3.500   0.0730   0.01124   0.00503  -0.1009   0.8351   0.0087
  -3.250   0.1001   0.01079   0.00449  -0.1007   0.8297   0.0090
  -3.000   0.1268   0.01023   0.00383  -0.1005   0.8238   0.0095
  -2.750   0.1535   0.00969   0.00320  -0.1003   0.8182   0.0106
  -2.500   0.1809   0.00937   0.00282  -0.1001   0.8111   0.0108
  -2.250   0.2083   0.00913   0.00248  -0.0999   0.8045   0.0109
  -2.000   0.2358   0.00892   0.00220  -0.0998   0.7971   0.0112
  -1.750   0.2635   0.00877   0.00195  -0.0997   0.7904   0.0116
  -1.500   0.2911   0.00864   0.00176  -0.0996   0.7828   0.0123
  -1.250   0.3188   0.00853   0.00160  -0.0995   0.7756   0.0141
  -1.000   0.3457   0.00814   0.00146  -0.0994   0.7676   0.0938
  -0.750   0.3723   0.00777   0.00138  -0.0994   0.7591   0.2016
  -0.500   0.3977   0.00718   0.00138  -0.0993   0.7496   0.4028
  -0.250   0.4219   0.00664   0.00143  -0.0988   0.7389   0.6066
   0.000   0.4475   0.00645   0.00143  -0.0983   0.7284   0.6879
   0.250   0.4712   0.00621   0.00145  -0.0973   0.7182   0.7883
   0.500   0.4960   0.00595   0.00146  -0.0962   0.7078   0.9236
   0.750   0.5392   0.00596   0.00141  -0.0995   0.6958   1.0000
   1.000   0.5657   0.00605   0.00142  -0.0992   0.6829   1.0000
   1.500   0.6182   0.00627   0.00147  -0.0986   0.6523   1.0000
   1.750   0.6441   0.00641   0.00151  -0.0982   0.6345   1.0000
   2.000   0.6699   0.00656   0.00158  -0.0978   0.6165   1.0000
   2.250   0.6957   0.00673   0.00165  -0.0974   0.5990   1.0000
   2.500   0.7214   0.00689   0.00174  -0.0970   0.5804   1.0000
   2.750   0.7469   0.00707   0.00184  -0.0966   0.5607   1.0000
   3.000   0.7721   0.00727   0.00197  -0.0962   0.5406   1.0000
   3.250   0.7972   0.00749   0.00210  -0.0957   0.5198   1.0000
   3.500   0.8219   0.00774   0.00225  -0.0952   0.4970   1.0000
   3.750   0.8461   0.00802   0.00242  -0.0946   0.4710   1.0000
   4.000   0.8702   0.00831   0.00261  -0.0940   0.4457   1.0000
   4.250   0.8946   0.00858   0.00282  -0.0934   0.4228   1.0000
   4.500   0.9189   0.00886   0.00303  -0.0929   0.4016   1.0000
   4.750   0.9428   0.00917   0.00326  -0.0923   0.3791   1.0000
   5.000   0.9648   0.00962   0.00354  -0.0914   0.3410   1.0000
   5.250   0.9835   0.01035   0.00393  -0.0901   0.2797   1.0000
   5.500   1.0046   0.01089   0.00430  -0.0891   0.2404   1.0000
   5.750   1.0259   0.01141   0.00467  -0.0882   0.2053   1.0000
   6.000   1.0466   0.01198   0.00507  -0.0871   0.1718   1.0000
   6.250   1.0644   0.01279   0.00559  -0.0858   0.1212   1.0000
   6.500   1.0822   0.01359   0.00615  -0.0843   0.0802   1.0000
   6.750   1.0997   0.01441   0.00679  -0.0828   0.0457   1.0000
   7.250   1.1338   0.01604   0.00819  -0.0796   0.0057   1.0000
   7.500   1.1541   0.01654   0.00873  -0.0785   0.0049   1.0000
   7.750   1.1737   0.01707   0.00933  -0.0773   0.0044   1.0000
   8.000   1.1924   0.01764   0.00999  -0.0759   0.0041   1.0000
   8.250   1.2093   0.01829   0.01074  -0.0742   0.0038   1.0000
   8.500   1.2250   0.01891   0.01148  -0.0722   0.0037   1.0000
   8.750   1.2395   0.01960   0.01226  -0.0702   0.0037   1.0000
   9.000   1.2528   0.02037   0.01313  -0.0680   0.0035   1.0000
   9.250   1.2648   0.02123   0.01409  -0.0658   0.0034   1.0000
   9.500   1.2762   0.02215   0.01510  -0.0635   0.0034   1.0000
   9.750   1.2860   0.02319   0.01624  -0.0611   0.0033   1.0000
  10.000   1.2951   0.02429   0.01746  -0.0588   0.0033   1.0000
  10.250   1.3019   0.02560   0.01888  -0.0563   0.0032   1.0000
  10.500   1.3092   0.02690   0.02030  -0.0540   0.0032   1.0000
  10.750   1.3150   0.02838   0.02189  -0.0517   0.0032   1.0000
  11.000   1.3201   0.02996   0.02362  -0.0496   0.0032   1.0000
  11.250   1.3236   0.03177   0.02557  -0.0474   0.0031   1.0000
  11.500   1.3276   0.03360   0.02753  -0.0454   0.0031   1.0000
  11.750   1.3305   0.03562   0.02969  -0.0436   0.0031   1.0000
  12.000   1.3333   0.03773   0.03194  -0.0419   0.0031   1.0000
  12.250   1.3348   0.04007   0.03443  -0.0404   0.0031   1.0000
  12.500   1.3368   0.04239   0.03690  -0.0392   0.0031   1.0000
  12.750   1.3368   0.04506   0.03973  -0.0380   0.0031   1.0000
  13.000   1.3361   0.04786   0.04269  -0.0371   0.0030   1.0000
  13.250   1.3345   0.05085   0.04584  -0.0364   0.0030   1.0000
  13.500   1.3339   0.05376   0.04889  -0.0362   0.0028   1.0000
  13.750   1.3260   0.05791   0.05326  -0.0359   0.0029   1.0000
  14.000   1.3240   0.06125   0.05673  -0.0363   0.0028   1.0000
  14.250   1.3175   0.06550   0.06115  -0.0370   0.0027   1.0000
  14.500   1.3121   0.06973   0.06552  -0.0381   0.0027   1.0000
  14.750   1.3025   0.07491   0.07089  -0.0396   0.0027   1.0000
  15.000   1.2942   0.08011   0.07624  -0.0416   0.0026   1.0000
  15.250   1.2824   0.08618   0.08250  -0.0440   0.0026   1.0000
  15.500   1.2695   0.09280   0.08931  -0.0470   0.0026   1.0000
  15.750   1.2568   0.09969   0.09637  -0.0505   0.0027   1.0000
  16.000   1.2435   0.10699   0.10383  -0.0544   0.0026   1.0000
  16.250   1.2292   0.11479   0.11180  -0.0587   0.0026   1.0000
  16.500   1.2140   0.12318   0.12035  -0.0635   0.0027   1.0000
  16.750   1.1984   0.13198   0.12931  -0.0687   0.0027   1.0000
  17.000   1.1810   0.14166   0.13915  -0.0745   0.0027   1.0000
  17.250   1.1668   0.15087   0.14850  -0.0802   0.0027   1.0000
  17.500   1.1496   0.16146   0.15922  -0.0866   0.0028   1.0000
  17.750   1.1312   0.17306   0.17094  -0.0936   0.0028   1.0000
  18.000   1.1045   0.18874   0.18676  -0.1024   0.0030   1.0000
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