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=1,000,000 Ncrit=5


Details Polar file
Airfoil: SOMERS S102 AIRFOIL (SHARP) (s102s-il)
Reynolds number: 1,000,000
Max Cl/Cd: 82.25 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s102s-il-1000000-n5.txt
Download as CSV file: xf-s102s-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.6368   0.06822   0.06611  -0.0678   1.0000   0.0037
 -13.250  -0.6563   0.06191   0.05969  -0.0709   1.0000   0.0037
 -13.000  -0.6665   0.05799   0.05569  -0.0722   1.0000   0.0037
 -12.500  -0.7023   0.04676   0.04408  -0.0778   0.9977   0.0036
 -12.250  -0.7078   0.04267   0.03980  -0.0800   0.9929   0.0036
 -12.000  -0.7229   0.03727   0.03409  -0.0823   0.9877   0.0036
 -11.750  -0.7202   0.03364   0.03022  -0.0846   0.9842   0.0036
 -11.500  -0.7134   0.03078   0.02714  -0.0861   0.9788   0.0036
 -11.250  -0.6983   0.02813   0.02426  -0.0884   0.9739   0.0036
 -10.750  -0.6615   0.02406   0.01979  -0.0915   0.9573   0.0036
 -10.500  -0.6436   0.02253   0.01808  -0.0919   0.9396   0.0036
 -10.250  -0.6259   0.02127   0.01658  -0.0918   0.9003   0.0036
 -10.000  -0.6170   0.02039   0.01541  -0.0896   0.8565   0.0036
  -9.750  -0.6084   0.01958   0.01439  -0.0873   0.8303   0.0036
  -9.500  -0.5990   0.01883   0.01347  -0.0850   0.8115   0.0036
  -9.250  -0.5843   0.01810   0.01260  -0.0834   0.7972   0.0036
  -9.000  -0.5679   0.01743   0.01179  -0.0821   0.7846   0.0036
  -8.750  -0.5503   0.01678   0.01103  -0.0810   0.7736   0.0036
  -8.500  -0.5328   0.01607   0.01021  -0.0799   0.7642   0.0037
  -8.000  -0.4961   0.01469   0.00865  -0.0778   0.7483   0.0037
  -7.750  -0.4755   0.01416   0.00803  -0.0770   0.7412   0.0038
  -7.500  -0.4545   0.01360   0.00740  -0.0763   0.7353   0.0038
  -7.250  -0.4325   0.01309   0.00683  -0.0758   0.7294   0.0039
  -7.000  -0.4094   0.01268   0.00636  -0.0753   0.7239   0.0040
  -6.750  -0.3854   0.01229   0.00592  -0.0750   0.7192   0.0041
  -6.500  -0.3607   0.01193   0.00552  -0.0748   0.7144   0.0042
  -6.250  -0.3357   0.01161   0.00516  -0.0746   0.7096   0.0044
  -6.000  -0.3102   0.01133   0.00483  -0.0745   0.7055   0.0045
  -5.750  -0.2840   0.01104   0.00451  -0.0745   0.7014   0.0048
  -5.500  -0.2577   0.01078   0.00422  -0.0745   0.6972   0.0052
  -5.250  -0.2310   0.01056   0.00395  -0.0745   0.6933   0.0055
  -5.000  -0.2045   0.01031   0.00368  -0.0745   0.6900   0.0064
  -4.750  -0.1771   0.01010   0.00346  -0.0746   0.6871   0.0073
  -4.500  -0.1496   0.00989   0.00324  -0.0748   0.6840   0.0092
  -4.250  -0.1221   0.00969   0.00305  -0.0749   0.6809   0.0126
  -4.000  -0.0946   0.00950   0.00287  -0.0751   0.6780   0.0187
  -3.750  -0.0669   0.00932   0.00270  -0.0753   0.6752   0.0273
  -3.500  -0.0393   0.00905   0.00253  -0.0755   0.6729   0.0494
  -3.250  -0.0122   0.00861   0.00230  -0.0759   0.6704   0.1085
  -3.000   0.0135   0.00766   0.00191  -0.0765   0.6677   0.2698
  -2.750   0.0385   0.00635   0.00153  -0.0773   0.6650   0.5444
  -2.500   0.0677   0.00640   0.00156  -0.0775   0.6626   0.5608
  -2.250   0.0969   0.00649   0.00164  -0.0778   0.6604   0.5748
  -2.000   0.1262   0.00664   0.00172  -0.0780   0.6582   0.5846
  -1.750   0.1555   0.00661   0.00168  -0.0784   0.6565   0.5859
  -1.500   0.1849   0.00660   0.00165  -0.0787   0.6545   0.5867
  -1.250   0.2140   0.00659   0.00162  -0.0790   0.6509   0.5874
  -1.000   0.2427   0.00661   0.00159  -0.0792   0.6453   0.5880
  -0.750   0.2716   0.00662   0.00157  -0.0795   0.6396   0.5887
  -0.500   0.3004   0.00663   0.00155  -0.0797   0.6329   0.5893
  -0.250   0.3288   0.00667   0.00154  -0.0799   0.6263   0.5900
   0.000   0.3579   0.00667   0.00153  -0.0801   0.6204   0.5907
   0.250   0.3863   0.00671   0.00153  -0.0803   0.6123   0.5914
   0.500   0.4149   0.00673   0.00153  -0.0805   0.6032   0.5921
   0.750   0.4430   0.00678   0.00153  -0.0806   0.5935   0.5928
   1.000   0.4713   0.00683   0.00155  -0.0808   0.5817   0.5935
   1.250   0.4991   0.00690   0.00157  -0.0808   0.5663   0.5943
   1.500   0.5260   0.00703   0.00160  -0.0807   0.5402   0.5952
   1.750   0.5463   0.00760   0.00178  -0.0795   0.4509   0.5961
   2.000   0.5656   0.00832   0.00210  -0.0781   0.3625   0.5968
   2.250   0.5878   0.00880   0.00233  -0.0773   0.3048   0.5975
   2.500   0.6114   0.00918   0.00252  -0.0767   0.2637   0.5981
   2.750   0.6356   0.00949   0.00269  -0.0763   0.2325   0.5988
   3.000   0.6602   0.00977   0.00286  -0.0758   0.2083   0.5993
   3.500   0.7103   0.01023   0.00317  -0.0751   0.1746   0.6009
   3.750   0.7354   0.01044   0.00333  -0.0748   0.1620   0.6018
   4.000   0.7609   0.01062   0.00348  -0.0745   0.1534   0.6027
   4.250   0.7860   0.01082   0.00365  -0.0741   0.1456   0.6037
   4.500   0.8118   0.01097   0.00381  -0.0739   0.1412   0.6046
   4.750   0.8369   0.01115   0.00398  -0.0735   0.1361   0.6055
   5.000   0.8617   0.01135   0.00417  -0.0731   0.1310   0.6065
   5.250   0.8870   0.01151   0.00434  -0.0728   0.1284   0.6075
   5.500   0.9118   0.01169   0.00453  -0.0724   0.1249   0.6085
   5.750   0.9359   0.01191   0.00473  -0.0719   0.1211   0.6095
   6.000   0.9597   0.01213   0.00495  -0.0713   0.1172   0.6106
   6.250   0.9841   0.01231   0.00515  -0.0709   0.1156   0.6118
   6.500   1.0081   0.01249   0.00537  -0.0703   0.1138   0.6129
   6.750   1.0315   0.01270   0.00559  -0.0697   0.1113   0.6141
   7.000   1.0541   0.01294   0.00583  -0.0689   0.1085   0.6150
   7.250   1.0760   0.01319   0.00609  -0.0680   0.1057   0.6159
   7.500   1.0967   0.01343   0.00635  -0.0669   0.1030   0.6172
   7.750   1.1174   0.01362   0.00659  -0.0658   0.1018   0.6185
   8.000   1.1375   0.01383   0.00684  -0.0645   0.1000   0.6199
   8.250   1.1571   0.01409   0.00714  -0.0632   0.0978   0.6213
   8.500   1.1763   0.01439   0.00745  -0.0619   0.0953   0.6227
   8.750   1.1948   0.01472   0.00779  -0.0605   0.0923   0.6242
   9.000   1.2137   0.01504   0.00815  -0.0592   0.0900   0.6258
   9.250   1.2332   0.01534   0.00850  -0.0581   0.0885   0.6274
   9.500   1.2520   0.01567   0.00886  -0.0568   0.0862   0.6289
   9.750   1.2699   0.01606   0.00926  -0.0555   0.0831   0.6304
  10.000   1.2867   0.01651   0.00971  -0.0540   0.0795   0.6318
  10.250   1.3048   0.01689   0.01015  -0.0528   0.0773   0.6336
  10.500   1.3221   0.01732   0.01062  -0.0514   0.0741   0.6357
  10.750   1.3375   0.01787   0.01116  -0.0499   0.0694   0.6377
  11.000   1.3532   0.01841   0.01172  -0.0485   0.0648   0.6400
  11.250   1.3666   0.01910   0.01239  -0.0469   0.0589   0.6425
  11.500   1.3821   0.01969   0.01303  -0.0455   0.0559   0.6450
  11.750   1.3952   0.02045   0.01379  -0.0440   0.0513   0.6474
  12.000   1.4067   0.02133   0.01466  -0.0424   0.0449   0.6500
  12.250   1.4179   0.02226   0.01560  -0.0408   0.0399   0.6529
  12.500   1.4275   0.02335   0.01668  -0.0391   0.0340   0.6560
  12.750   1.4404   0.02422   0.01760  -0.0379   0.0316   0.6593
  13.000   1.4495   0.02542   0.01880  -0.0364   0.0266   0.6624
  13.500   1.4700   0.02771   0.02116  -0.0338   0.0207   0.6696
  13.750   1.4796   0.02895   0.02244  -0.0326   0.0183   0.6740
  14.000   1.4899   0.03016   0.02370  -0.0316   0.0166   0.6785
  14.250   1.4979   0.03159   0.02517  -0.0305   0.0142   0.6830
  14.500   1.5060   0.03303   0.02667  -0.0294   0.0125   0.6886
  14.750   1.5143   0.03451   0.02822  -0.0285   0.0110   0.6946
  15.000   1.5222   0.03604   0.02983  -0.0276   0.0100   0.7008
  15.250   1.5288   0.03771   0.03157  -0.0268   0.0088   0.7085
  15.500   1.5357   0.03940   0.03335  -0.0261   0.0081   0.7167
  15.750   1.5412   0.04128   0.03532  -0.0254   0.0073   0.7265
  16.000   1.5467   0.04319   0.03733  -0.0249   0.0066   0.7380
  16.250   1.5516   0.04520   0.03945  -0.0244   0.0062   0.7525
  16.500   1.5550   0.04741   0.04180  -0.0240   0.0057   0.7733
  16.750   1.5582   0.04968   0.04423  -0.0237   0.0052   0.8039
  17.000   1.5600   0.05171   0.04668  -0.0232   0.0050   0.9883
  17.250   1.5609   0.05434   0.04940  -0.0230   0.0048   1.0000
  17.500   1.5606   0.05730   0.05245  -0.0232   0.0044   1.0000
  17.750   1.5588   0.06055   0.05579  -0.0235   0.0041   1.0000
  18.000   1.5568   0.06394   0.05927  -0.0241   0.0040   1.0000
  18.250   1.5542   0.06750   0.06293  -0.0248   0.0038   1.0000
  18.500   1.5493   0.07150   0.06704  -0.0258   0.0036   1.0000
  18.750   1.5433   0.07584   0.07149  -0.0271   0.0035   1.0000
  19.000   1.5339   0.08085   0.07663  -0.0289   0.0032   1.0000
  19.250   1.5227   0.08637   0.08228  -0.0311   0.0031   1.0000
<< Back to SOMERS S102 AIRFOIL (SHARP) (s102s-il)

Polar data table (+)

Polar graphs


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