Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S1012 (s1012-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S1012 (s1012-il)
Reynolds number: 500,000
Max Cl/Cd: 56.79 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1012-il-500000-n5.txt
Download as CSV file: xf-s1012-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1012                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -18.250  -1.0833   0.10294   0.09955  -0.0179   1.0000   0.0142
 -18.000  -1.1205   0.09166   0.08808  -0.0245   1.0000   0.0141
 -17.750  -1.1544   0.08113   0.07736  -0.0308   1.0000   0.0140
 -17.500  -1.1801   0.07226   0.06831  -0.0363   1.0000   0.0140
 -17.250  -1.2013   0.06467   0.06054  -0.0408   1.0000   0.0141
 -17.000  -1.2163   0.05866   0.05436  -0.0441   1.0000   0.0142
 -16.750  -1.2284   0.05361   0.04917  -0.0464   1.0000   0.0143
 -16.500  -1.2364   0.04957   0.04499  -0.0478   1.0000   0.0144
 -16.250  -1.2417   0.04619   0.04147  -0.0486   1.0000   0.0146
 -16.000  -1.2445   0.04334   0.03850  -0.0488   1.0000   0.0149
 -15.750  -1.2459   0.04079   0.03582  -0.0486   1.0000   0.0152
 -15.500  -1.2446   0.03864   0.03356  -0.0481   1.0000   0.0155
 -15.250  -1.2424   0.03666   0.03144  -0.0474   1.0000   0.0157
 -15.000  -1.2409   0.03472   0.02940  -0.0464   1.0000   0.0160
 -14.750  -1.2391   0.03288   0.02747  -0.0452   1.0000   0.0163
 -14.500  -1.2340   0.03134   0.02586  -0.0441   1.0000   0.0167
 -14.250  -1.2276   0.02996   0.02440  -0.0428   1.0000   0.0170
 -14.000  -1.2194   0.02874   0.02310  -0.0415   1.0000   0.0175
 -13.750  -1.2099   0.02763   0.02191  -0.0402   1.0000   0.0180
 -13.500  -1.1992   0.02661   0.02082  -0.0389   1.0000   0.0186
 -13.250  -1.1880   0.02565   0.01975  -0.0375   1.0000   0.0192
 -13.000  -1.1757   0.02478   0.01879  -0.0361   1.0000   0.0196
 -12.750  -1.1655   0.02377   0.01774  -0.0345   1.0000   0.0203
 -12.500  -1.1527   0.02294   0.01687  -0.0330   1.0000   0.0210
 -12.250  -1.1388   0.02220   0.01607  -0.0316   1.0000   0.0217
 -12.000  -1.1240   0.02151   0.01533  -0.0303   1.0000   0.0225
 -11.500  -1.0819   0.02015   0.01381  -0.0298   0.9607   0.0244
 -11.250  -1.0565   0.01945   0.01306  -0.0304   0.9398   0.0259
 -11.000  -1.0388   0.01894   0.01247  -0.0291   0.9232   0.0272
 -10.500  -1.0061   0.01808   0.01141  -0.0257   0.9023   0.0296
 -10.250  -0.9903   0.01763   0.01090  -0.0238   0.8950   0.0311
 -10.000  -0.9721   0.01722   0.01046  -0.0224   0.8890   0.0328
  -9.750  -0.9524   0.01686   0.01001  -0.0212   0.8840   0.0345
  -9.250  -0.9114   0.01606   0.00913  -0.0191   0.8763   0.0384
  -9.000  -0.8896   0.01570   0.00875  -0.0183   0.8728   0.0407
  -8.750  -0.8673   0.01539   0.00837  -0.0175   0.8695   0.0426
  -8.500  -0.8457   0.01501   0.00797  -0.0166   0.8666   0.0450
  -8.000  -0.7997   0.01440   0.00729  -0.0152   0.8617   0.0504
  -7.750  -0.7765   0.01407   0.00695  -0.0146   0.8592   0.0534
  -7.500  -0.7530   0.01376   0.00665  -0.0140   0.8566   0.0571
  -7.250  -0.7289   0.01350   0.00635  -0.0135   0.8541   0.0604
  -7.000  -0.7052   0.01321   0.00605  -0.0129   0.8519   0.0641
  -6.750  -0.6811   0.01294   0.00578  -0.0123   0.8501   0.0684
  -6.500  -0.6563   0.01273   0.00552  -0.0118   0.8484   0.0721
  -6.250  -0.6318   0.01244   0.00527  -0.0114   0.8466   0.0774
  -6.000  -0.6067   0.01221   0.00504  -0.0110   0.8448   0.0825
  -5.750  -0.5815   0.01197   0.00481  -0.0106   0.8430   0.0879
  -5.500  -0.5563   0.01174   0.00460  -0.0103   0.8413   0.0948
  -5.250  -0.5308   0.01153   0.00440  -0.0099   0.8396   0.1012
  -5.000  -0.5054   0.01131   0.00421  -0.0096   0.8378   0.1095
  -4.750  -0.4800   0.01109   0.00402  -0.0092   0.8360   0.1185
  -4.500  -0.4542   0.01091   0.00384  -0.0089   0.8345   0.1274
  -4.250  -0.4286   0.01071   0.00368  -0.0085   0.8332   0.1389
  -4.000  -0.4029   0.01050   0.00353  -0.0082   0.8319   0.1528
  -3.750  -0.3770   0.01029   0.00339  -0.0080   0.8304   0.1681
  -3.500  -0.3511   0.01008   0.00326  -0.0077   0.8289   0.1866
  -3.250  -0.3257   0.00983   0.00312  -0.0074   0.8271   0.2106
  -3.000  -0.3003   0.00958   0.00300  -0.0071   0.8253   0.2384
  -2.750  -0.2754   0.00929   0.00287  -0.0067   0.8238   0.2764
  -2.500  -0.2509   0.00897   0.00274  -0.0062   0.8221   0.3226
  -2.250  -0.2269   0.00862   0.00260  -0.0057   0.8204   0.3780
  -2.000  -0.2044   0.00816   0.00245  -0.0048   0.8188   0.4529
  -1.750  -0.1829   0.00765   0.00229  -0.0038   0.8171   0.5414
  -1.500  -0.1624   0.00714   0.00225  -0.0024   0.8151   0.6464
  -1.250  -0.1370   0.00706   0.00239  -0.0017   0.8129   0.7062
  -1.000  -0.1095   0.00706   0.00244  -0.0015   0.8094   0.7288
  -0.750  -0.0823   0.00703   0.00237  -0.0010   0.8018   0.7432
  -0.500  -0.0553   0.00695   0.00226  -0.0006   0.7885   0.7536
  -0.250  -0.0279   0.00692   0.00222  -0.0002   0.7773   0.7616
   0.000   0.0000   0.00691   0.00218   0.0000   0.7698   0.7698
   0.250   0.0279   0.00692   0.00222   0.0002   0.7618   0.7772
   0.500   0.0553   0.00695   0.00226   0.0006   0.7535   0.7885
   0.750   0.0822   0.00703   0.00237   0.0010   0.7431   0.8018
   1.000   0.1095   0.00706   0.00244   0.0015   0.7290   0.8094
   1.250   0.1370   0.00706   0.00239   0.0017   0.7064   0.8129
   1.750   0.1828   0.00765   0.00229   0.0038   0.5403   0.8171
   2.000   0.2043   0.00817   0.00245   0.0049   0.4516   0.8188
   2.250   0.2270   0.00861   0.00260   0.0057   0.3784   0.8204
   2.500   0.2509   0.00897   0.00274   0.0062   0.3226   0.8221
   2.750   0.2754   0.00929   0.00287   0.0067   0.2771   0.8238
   3.000   0.3003   0.00958   0.00300   0.0071   0.2387   0.8253
   3.250   0.3257   0.00983   0.00312   0.0074   0.2107   0.8271
   3.500   0.3511   0.01008   0.00326   0.0078   0.1864   0.8289
   3.750   0.3770   0.01029   0.00339   0.0080   0.1681   0.8304
   4.000   0.4029   0.01050   0.00353   0.0082   0.1528   0.8319
   4.250   0.4286   0.01071   0.00368   0.0086   0.1388   0.8332
   4.500   0.4542   0.01091   0.00384   0.0089   0.1273   0.8345
   4.750   0.4800   0.01109   0.00402   0.0092   0.1184   0.8360
   5.000   0.5054   0.01131   0.00421   0.0096   0.1094   0.8378
   5.250   0.5308   0.01152   0.00440   0.0099   0.1013   0.8396
   5.500   0.5563   0.01174   0.00460   0.0103   0.0948   0.8413
   5.750   0.5815   0.01197   0.00481   0.0106   0.0879   0.8430
   6.000   0.6066   0.01221   0.00504   0.0110   0.0825   0.8448
   6.250   0.6318   0.01244   0.00527   0.0114   0.0774   0.8466
   6.500   0.6563   0.01273   0.00552   0.0118   0.0721   0.8483
   6.750   0.6810   0.01294   0.00578   0.0123   0.0685   0.8500
   7.000   0.7052   0.01321   0.00605   0.0129   0.0643   0.8519
   7.250   0.7289   0.01350   0.00635   0.0135   0.0603   0.8541
   7.500   0.7530   0.01376   0.00664   0.0140   0.0571   0.8566
   7.750   0.7765   0.01407   0.00695   0.0146   0.0534   0.8592
   8.000   0.7998   0.01440   0.00729   0.0152   0.0505   0.8617
   8.500   0.8457   0.01501   0.00797   0.0166   0.0450   0.8666
   8.750   0.8673   0.01539   0.00837   0.0175   0.0426   0.8695
   9.000   0.8897   0.01570   0.00874   0.0183   0.0407   0.8727
   9.250   0.9115   0.01605   0.00913   0.0191   0.0383   0.8763
   9.750   0.9525   0.01685   0.01001   0.0212   0.0344   0.8840
  10.000   0.9722   0.01722   0.01045   0.0224   0.0328   0.8890
  10.250   0.9904   0.01762   0.01090   0.0238   0.0311   0.8950
  10.500   1.0063   0.01808   0.01140   0.0257   0.0296   0.9023
  11.000   1.0389   0.01895   0.01247   0.0291   0.0272   0.9233
  11.250   1.0568   0.01945   0.01305   0.0303   0.0259   0.9399
  11.500   1.0823   0.02015   0.01381   0.0298   0.0244   0.9609
  12.000   1.1243   0.02151   0.01532   0.0302   0.0226   1.0000
  12.250   1.1391   0.02220   0.01607   0.0316   0.0217   1.0000
  12.500   1.1530   0.02295   0.01687   0.0330   0.0210   1.0000
  12.750   1.1658   0.02377   0.01774   0.0344   0.0203   1.0000
  13.000   1.1763   0.02477   0.01877   0.0360   0.0196   1.0000
  13.250   1.1882   0.02567   0.01977   0.0374   0.0191   1.0000
  13.500   1.1999   0.02660   0.02080   0.0388   0.0185   1.0000
  13.750   1.2109   0.02759   0.02187   0.0401   0.0180   1.0000
  14.000   1.2200   0.02872   0.02308   0.0414   0.0175   1.0000
  14.250   1.2279   0.02997   0.02441   0.0427   0.0172   1.0000
  14.500   1.2348   0.03132   0.02584   0.0440   0.0167   1.0000
  14.750   1.2395   0.03288   0.02748   0.0452   0.0163   1.0000
  15.000   1.2408   0.03476   0.02944   0.0464   0.0159   1.0000
  15.250   1.2426   0.03668   0.03147   0.0473   0.0157   1.0000
  15.500   1.2462   0.03854   0.03346   0.0480   0.0154   1.0000
  15.750   1.2471   0.04072   0.03575   0.0485   0.0151   1.0000
  16.000   1.2461   0.04323   0.03839   0.0487   0.0149   1.0000
  16.250   1.2427   0.04614   0.04143   0.0485   0.0146   1.0000
  16.500   1.2380   0.04945   0.04486   0.0478   0.0144   1.0000
  16.750   1.2287   0.05367   0.04922   0.0463   0.0143   1.0000
  17.000   1.2173   0.05860   0.05431   0.0440   0.0142   1.0000
  17.250   1.2040   0.06436   0.06022   0.0408   0.0140   1.0000
  17.500   1.1835   0.07183   0.06787   0.0364   0.0140   1.0000
  17.750   1.1564   0.08090   0.07713   0.0308   0.0140   1.0000
  18.000   1.1221   0.09156   0.08798   0.0244   0.0140   1.0000
  18.250   1.0853   0.10275   0.09934   0.0179   0.0142   1.0000
<< Back to S1012 (s1012-il)

Polar data table (+)

Polar graphs


<< Back to S1012 (s1012-il)