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

SOMERS S102 AIRFOIL (SHARP) (s102s-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: SOMERS S102 AIRFOIL (SHARP) (s102s-il)
Reynolds number: 500,000
Max Cl/Cd: 69.83 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s102s-il-500000-n5.txt
Download as CSV file: xf-s102s-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SOMERS S102 AIRFOIL (SHARP)                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.5822   0.06174   0.05893  -0.0703   1.0000   0.0055
 -11.750  -0.6060   0.05681   0.05389  -0.0712   1.0000   0.0055
 -11.500  -0.6243   0.05235   0.04929  -0.0722   0.9994   0.0054
 -11.250  -0.6352   0.04672   0.04341  -0.0762   0.9949   0.0054
 -11.000  -0.6444   0.04174   0.03816  -0.0789   0.9889   0.0054
 -10.750  -0.6456   0.03710   0.03317  -0.0819   0.9838   0.0053
 -10.500  -0.6426   0.03357   0.02934  -0.0832   0.9757   0.0053
 -10.250  -0.6318   0.03041   0.02585  -0.0847   0.9682   0.0053
 -10.000  -0.6166   0.02795   0.02312  -0.0857   0.9589   0.0053
  -9.500  -0.5830   0.02416   0.01883  -0.0855   0.9311   0.0053
  -9.250  -0.5596   0.02261   0.01704  -0.0859   0.9128   0.0053
  -9.000  -0.5361   0.02136   0.01557  -0.0861   0.8893   0.0053
  -8.750  -0.5159   0.02034   0.01431  -0.0854   0.8658   0.0054
  -8.500  -0.4979   0.01948   0.01326  -0.0842   0.8458   0.0054
  -8.250  -0.4799   0.01876   0.01238  -0.0830   0.8294   0.0055
  -8.000  -0.4632   0.01792   0.01139  -0.0817   0.8156   0.0055
  -7.500  -0.4279   0.01654   0.00980  -0.0793   0.7923   0.0057
  -7.250  -0.4087   0.01595   0.00913  -0.0784   0.7830   0.0059
  -7.000  -0.3885   0.01543   0.00852  -0.0776   0.7743   0.0060
  -6.750  -0.3672   0.01494   0.00797  -0.0769   0.7671   0.0062
  -6.500  -0.3453   0.01447   0.00743  -0.0763   0.7601   0.0064
  -6.250  -0.3228   0.01404   0.00692  -0.0758   0.7541   0.0068
  -6.000  -0.2993   0.01362   0.00644  -0.0754   0.7483   0.0071
  -5.750  -0.2753   0.01325   0.00599  -0.0751   0.7428   0.0076
  -5.500  -0.2513   0.01285   0.00555  -0.0748   0.7380   0.0085
  -5.250  -0.2259   0.01253   0.00518  -0.0746   0.7333   0.0093
  -5.000  -0.2004   0.01220   0.00482  -0.0745   0.7286   0.0109
  -4.750  -0.1745   0.01193   0.00450  -0.0744   0.7242   0.0133
  -4.500  -0.1485   0.01163   0.00421  -0.0745   0.7202   0.0192
  -4.250  -0.1220   0.01132   0.00394  -0.0745   0.7162   0.0302
  -4.000  -0.0956   0.01100   0.00368  -0.0746   0.7126   0.0485
  -3.750  -0.0700   0.01049   0.00338  -0.0748   0.7092   0.1033
  -3.500  -0.0474   0.00917   0.00276  -0.0754   0.7062   0.2970
  -3.250  -0.0232   0.00810   0.00257  -0.0759   0.7031   0.5517
  -3.000   0.0058   0.00823   0.00268  -0.0760   0.7001   0.5716
  -2.750   0.0349   0.00839   0.00277  -0.0762   0.6972   0.5855
  -2.500   0.0636   0.00868   0.00302  -0.0762   0.6944   0.6009
  -2.250   0.0923   0.00873   0.00304  -0.0763   0.6917   0.6043
  -2.000   0.1214   0.00871   0.00296  -0.0766   0.6892   0.6050
  -1.750   0.1506   0.00869   0.00290  -0.0769   0.6867   0.6058
  -1.500   0.1797   0.00867   0.00285  -0.0773   0.6843   0.6065
  -1.250   0.2088   0.00867   0.00281  -0.0776   0.6819   0.6075
  -1.000   0.2378   0.00867   0.00277  -0.0779   0.6797   0.6085
  -0.750   0.2669   0.00868   0.00274  -0.0782   0.6773   0.6093
  -0.500   0.2956   0.00870   0.00270  -0.0784   0.6734   0.6101
  -0.250   0.3240   0.00867   0.00266  -0.0786   0.6669   0.6109
   0.000   0.3522   0.00869   0.00261  -0.0787   0.6600   0.6117
   0.250   0.3805   0.00869   0.00259  -0.0789   0.6530   0.6125
   0.500   0.4087   0.00870   0.00256  -0.0790   0.6460   0.6133
   0.750   0.4370   0.00872   0.00255  -0.0791   0.6401   0.6141
   1.000   0.4651   0.00873   0.00255  -0.0792   0.6321   0.6148
   1.250   0.4929   0.00876   0.00254  -0.0793   0.6232   0.6156
   1.500   0.5203   0.00878   0.00254  -0.0792   0.6125   0.6166
   1.750   0.5479   0.00880   0.00255  -0.0793   0.6012   0.6175
   2.000   0.5751   0.00883   0.00258  -0.0792   0.5886   0.6183
   2.250   0.6021   0.00888   0.00260  -0.0791   0.5728   0.6192
   2.500   0.6278   0.00899   0.00264  -0.0787   0.5468   0.6200
   2.750   0.6474   0.00939   0.00274  -0.0773   0.4745   0.6209
   3.000   0.6613   0.01028   0.00314  -0.0750   0.3759   0.6218
   3.250   0.6798   0.01092   0.00349  -0.0736   0.3117   0.6227
   3.500   0.7003   0.01142   0.00379  -0.0725   0.2664   0.6237
   3.750   0.7220   0.01183   0.00404  -0.0716   0.2337   0.6248
   4.000   0.7445   0.01217   0.00428  -0.0709   0.2094   0.6258
   4.500   0.7903   0.01279   0.00475  -0.0695   0.1770   0.6280
   4.750   0.8136   0.01305   0.00498  -0.0688   0.1662   0.6291
   5.000   0.8366   0.01332   0.00521  -0.0682   0.1581   0.6301
   5.250   0.8600   0.01356   0.00545  -0.0675   0.1517   0.6312
   5.750   0.9053   0.01406   0.00596  -0.0660   0.1418   0.6337
   6.000   0.9276   0.01430   0.00624  -0.0652   0.1376   0.6350
   6.250   0.9486   0.01460   0.00654  -0.0642   0.1331   0.6364
   6.500   0.9693   0.01487   0.00683  -0.0631   0.1297   0.6377
   6.750   0.9895   0.01510   0.00712  -0.0619   0.1271   0.6391
   7.000   1.0087   0.01537   0.00743  -0.0605   0.1244   0.6405
   7.250   1.0276   0.01569   0.00777  -0.0592   0.1217   0.6420
   7.500   1.0457   0.01606   0.00816  -0.0577   0.1187   0.6436
   7.750   1.0639   0.01644   0.00857  -0.0563   0.1161   0.6452
   8.000   1.0836   0.01676   0.00894  -0.0552   0.1143   0.6467
   8.250   1.1027   0.01711   0.00935  -0.0540   0.1119   0.6482
   8.500   1.1212   0.01749   0.00978  -0.0527   0.1094   0.6499
   8.750   1.1387   0.01792   0.01025  -0.0514   0.1069   0.6516
   9.000   1.1549   0.01843   0.01079  -0.0499   0.1042   0.6535
   9.250   1.1724   0.01888   0.01131  -0.0486   0.1023   0.6555
   9.500   1.1909   0.01929   0.01181  -0.0475   0.1003   0.6577
   9.750   1.2087   0.01975   0.01233  -0.0463   0.0978   0.6600
  10.000   1.2257   0.02027   0.01288  -0.0451   0.0951   0.6624
  10.500   1.2570   0.02148   0.01420  -0.0426   0.0898   0.6676
  10.750   1.2744   0.02200   0.01482  -0.0415   0.0875   0.6705
  11.000   1.2908   0.02260   0.01549  -0.0405   0.0845   0.6737
  11.250   1.3061   0.02329   0.01621  -0.0394   0.0812   0.6770
  11.500   1.3209   0.02403   0.01700  -0.0382   0.0781   0.6802
  11.750   1.3368   0.02471   0.01777  -0.0373   0.0746   0.6837
  12.000   1.3512   0.02551   0.01861  -0.0362   0.0701   0.6877
  12.250   1.3653   0.02636   0.01951  -0.0352   0.0660   0.6921
  12.750   1.3910   0.02829   0.02153  -0.0331   0.0571   0.7017
  13.000   1.4032   0.02934   0.02264  -0.0321   0.0522   0.7075
  13.250   1.4140   0.03052   0.02387  -0.0311   0.0484   0.7136
  13.500   1.4248   0.03173   0.02515  -0.0301   0.0444   0.7206
  14.000   1.4437   0.03444   0.02801  -0.0283   0.0372   0.7380
  14.250   1.4514   0.03599   0.02963  -0.0273   0.0339   0.7488
  14.500   1.4595   0.03751   0.03126  -0.0265   0.0308   0.7630
  14.750   1.4654   0.03924   0.03310  -0.0256   0.0281   0.7818
  15.000   1.4717   0.04091   0.03494  -0.0248   0.0257   0.8111
  15.250   1.4750   0.04265   0.03698  -0.0237   0.0231   0.9318
  15.500   1.4789   0.04459   0.03900  -0.0230   0.0211   1.0000
  15.750   1.4810   0.04699   0.04144  -0.0226   0.0187   1.0000
  16.000   1.4834   0.04942   0.04394  -0.0223   0.0165   1.0000
  16.250   1.4844   0.05208   0.04668  -0.0221   0.0152   1.0000
  16.500   1.4859   0.05476   0.04946  -0.0221   0.0139   1.0000
  16.750   1.4835   0.05798   0.05274  -0.0222   0.0124   1.0000
  17.000   1.4826   0.06114   0.05601  -0.0225   0.0115   1.0000
  17.250   1.4806   0.06454   0.05953  -0.0231   0.0108   1.0000
  17.500   1.4746   0.06858   0.06368  -0.0239   0.0099   1.0000
  17.750   1.4686   0.07281   0.06803  -0.0250   0.0093   1.0000
  18.000   1.4624   0.07725   0.07260  -0.0264   0.0090   1.0000
  18.250   1.4532   0.08233   0.07783  -0.0283   0.0086   1.0000
  18.500   1.4409   0.08814   0.08378  -0.0307   0.0081   1.0000
  18.750   1.4263   0.09464   0.09044  -0.0337   0.0080   1.0000
  19.000   1.4080   0.10211   0.09809  -0.0374   0.0078   1.0000
  19.250   1.3857   0.11064   0.10680  -0.0420   0.0077   1.0000
<< Back to SOMERS S102 AIRFOIL (SHARP) (s102s-il)

Polar data table (+)

Polar graphs


<< Back to SOMERS S102 AIRFOIL (SHARP) (s102s-il)