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SA7035 (sa7035-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: SA7035 (sa7035-il)
Reynolds number: 500,000
Max Cl/Cd: 94.89 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7035-il-500000.txt
Download as CSV file: xf-sa7035-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7035                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4020   0.08318   0.08099  -0.0322   1.0000   0.0166
  -8.250  -0.4023   0.07944   0.07728  -0.0342   1.0000   0.0168
  -8.000  -0.4046   0.07564   0.07353  -0.0360   1.0000   0.0170
  -7.750  -0.4138   0.07225   0.07019  -0.0369   1.0000   0.0170
  -7.500  -0.4275   0.06889   0.06689  -0.0377   1.0000   0.0170
  -7.250  -0.4420   0.06551   0.06353  -0.0378   1.0000   0.0169
  -7.000  -0.4366   0.05893   0.05684  -0.0435   0.9982   0.0172
  -6.750  -0.4112   0.05128   0.04892  -0.0524   0.9940   0.0173
  -6.500  -0.3997   0.04041   0.03760  -0.0604   0.9873   0.0180
  -6.250  -0.3720   0.03689   0.03396  -0.0641   0.9846   0.0187
  -6.000  -0.3435   0.03400   0.03090  -0.0670   0.9811   0.0197
  -5.750  -0.3148   0.03077   0.02739  -0.0692   0.9767   0.0214
  -5.500  -0.2753   0.03039   0.02660  -0.0708   0.9742   0.0247
  -5.250  -0.2496   0.01793   0.01277  -0.0717   0.9709   0.0123
  -5.000  -0.2218   0.01584   0.01039  -0.0717   0.9656   0.0124
  -4.750  -0.1916   0.01419   0.00854  -0.0722   0.9612   0.0126
  -4.500  -0.1599   0.01303   0.00729  -0.0730   0.9575   0.0134
  -4.250  -0.1341   0.01252   0.00676  -0.0726   0.9503   0.0148
  -4.000  -0.1065   0.01167   0.00582  -0.0722   0.9444   0.0153
  -3.750  -0.0820   0.01094   0.00499  -0.0713   0.9365   0.0157
  -3.500  -0.0562   0.01032   0.00428  -0.0705   0.9297   0.0164
  -3.250  -0.0313   0.00978   0.00364  -0.0696   0.9212   0.0179
  -3.000  -0.0055   0.00926   0.00305  -0.0689   0.9142   0.0241
  -2.750   0.0185   0.00839   0.00260  -0.0682   0.9046   0.1227
  -2.500   0.0436   0.00789   0.00239  -0.0677   0.8957   0.2123
  -2.250   0.0683   0.00728   0.00221  -0.0672   0.8868   0.3437
  -2.000   0.0927   0.00672   0.00210  -0.0666   0.8758   0.4831
  -1.750   0.1182   0.00642   0.00200  -0.0660   0.8649   0.5656
  -1.500   0.1436   0.00617   0.00192  -0.0653   0.8535   0.6417
  -1.250   0.1690   0.00597   0.00185  -0.0645   0.8416   0.7029
  -1.000   0.1938   0.00579   0.00180  -0.0635   0.8287   0.7648
  -0.750   0.2176   0.00563   0.00177  -0.0622   0.8149   0.8256
  -0.500   0.2403   0.00552   0.00174  -0.0606   0.8001   0.8815
  -0.250   0.2651   0.00548   0.00170  -0.0593   0.7842   0.9310
   0.000   0.2997   0.00549   0.00163  -0.0604   0.7671   0.9665
   0.250   0.3412   0.00552   0.00154  -0.0632   0.7491   0.9883
   0.500   0.3802   0.00558   0.00147  -0.0656   0.7308   1.0000
   0.750   0.4044   0.00567   0.00146  -0.0648   0.7117   1.0000
   1.000   0.4290   0.00578   0.00146  -0.0641   0.6927   1.0000
   1.250   0.4539   0.00591   0.00147  -0.0635   0.6734   1.0000
   1.500   0.4794   0.00603   0.00150  -0.0629   0.6534   1.0000
   1.750   0.5048   0.00618   0.00153  -0.0624   0.6328   1.0000
   2.000   0.5305   0.00633   0.00158  -0.0620   0.6110   1.0000
   2.500   0.5822   0.00665   0.00173  -0.0612   0.5692   1.0000
   2.750   0.6082   0.00683   0.00181  -0.0608   0.5488   1.0000
   3.000   0.6343   0.00701   0.00191  -0.0604   0.5276   1.0000
   3.250   0.6602   0.00721   0.00204  -0.0601   0.5064   1.0000
   3.500   0.6862   0.00741   0.00216  -0.0598   0.4848   1.0000
   4.000   0.7379   0.00785   0.00244  -0.0591   0.4397   1.0000
   4.250   0.7636   0.00810   0.00262  -0.0588   0.4185   1.0000
   4.500   0.7894   0.00834   0.00279  -0.0585   0.3963   1.0000
   4.750   0.8150   0.00860   0.00299  -0.0581   0.3753   1.0000
   5.000   0.8407   0.00886   0.00319  -0.0578   0.3544   1.0000
   5.250   0.8660   0.00916   0.00343  -0.0575   0.3321   1.0000
   5.500   0.8911   0.00948   0.00367  -0.0571   0.3087   1.0000
   5.750   0.9161   0.00981   0.00393  -0.0567   0.2843   1.0000
   6.000   0.9408   0.01017   0.00421  -0.0563   0.2609   1.0000
   6.250   0.9653   0.01055   0.00453  -0.0559   0.2387   1.0000
   6.500   0.9900   0.01092   0.00485  -0.0555   0.2182   1.0000
   7.000   1.0381   0.01176   0.00557  -0.0545   0.1762   1.0000
   7.500   1.0845   0.01276   0.00642  -0.0534   0.1326   1.0000
   7.750   1.1070   0.01332   0.00689  -0.0527   0.1114   1.0000
   8.000   1.1292   0.01391   0.00740  -0.0520   0.0923   1.0000
   8.250   1.1507   0.01454   0.00797  -0.0513   0.0742   1.0000
   8.500   1.1716   0.01523   0.00859  -0.0504   0.0577   1.0000
   8.750   1.1919   0.01596   0.00929  -0.0494   0.0452   1.0000
   9.000   1.2118   0.01671   0.01003  -0.0484   0.0356   1.0000
   9.250   1.2309   0.01751   0.01084  -0.0473   0.0275   1.0000
   9.500   1.2478   0.01849   0.01186  -0.0458   0.0212   1.0000
   9.750   1.2637   0.01949   0.01288  -0.0442   0.0168   1.0000
  10.000   1.2804   0.02037   0.01385  -0.0428   0.0144   1.0000
  10.250   1.2961   0.02126   0.01481  -0.0412   0.0125   1.0000
  10.500   1.3013   0.02289   0.01655  -0.0383   0.0110   1.0000
  10.750   1.3093   0.02398   0.01777  -0.0355   0.0103   1.0000
  11.000   1.3176   0.02503   0.01897  -0.0330   0.0094   1.0000
  11.250   1.3240   0.02623   0.02026  -0.0305   0.0088   1.0000
  11.500   1.3294   0.02754   0.02165  -0.0281   0.0082   1.0000
  11.750   1.3301   0.02926   0.02347  -0.0256   0.0077   1.0000
  12.000   1.3187   0.03215   0.02653  -0.0225   0.0071   1.0000
  12.250   1.3242   0.03376   0.02828  -0.0211   0.0068   1.0000
  12.500   1.3279   0.03561   0.03026  -0.0199   0.0065   1.0000
  12.750   1.3285   0.03788   0.03267  -0.0188   0.0062   1.0000
  13.000   1.3251   0.04075   0.03569  -0.0179   0.0060   1.0000
  13.250   1.3227   0.04368   0.03877  -0.0176   0.0059   1.0000
  13.500   1.3190   0.04694   0.04218  -0.0176   0.0057   1.0000
  13.750   1.3135   0.05064   0.04603  -0.0180   0.0056   1.0000
  14.000   1.3101   0.05422   0.04973  -0.0189   0.0054   1.0000
  14.250   1.3035   0.05848   0.05413  -0.0202   0.0053   1.0000
  14.500   1.2955   0.06315   0.05895  -0.0218   0.0052   1.0000
  14.750   1.2859   0.06829   0.06424  -0.0239   0.0052   1.0000
  15.000   1.2749   0.07392   0.07002  -0.0264   0.0051   1.0000
  15.250   1.2656   0.07949   0.07572  -0.0292   0.0050   1.0000
  15.500   1.2526   0.08597   0.08235  -0.0324   0.0050   1.0000
  15.750   1.2394   0.09276   0.08929  -0.0360   0.0049   1.0000
  16.000   1.2260   0.09985   0.09654  -0.0398   0.0050   1.0000
  16.250   1.2123   0.10727   0.10411  -0.0439   0.0050   1.0000
  16.500   1.1988   0.11486   0.11183  -0.0483   0.0049   1.0000
  16.750   1.1827   0.12341   0.12058  -0.0532   0.0051   1.0000
  17.000   1.1696   0.13143   0.12871  -0.0580   0.0050   1.0000
  17.250   1.1548   0.14016   0.13758  -0.0632   0.0050   1.0000
  17.500   1.1391   0.14944   0.14701  -0.0688   0.0050   1.0000
  17.750   1.1103   0.16319   0.16099  -0.0771   0.0053   1.0000
  18.000   1.0050   0.20813   0.20613  -0.1004   0.0070   1.0000
  18.250   1.0031   0.21601   0.21399  -0.1042   0.0072   1.0000
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