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SOMERS S102 AIRFOIL (SHARP) (s102s-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SOMERS S102 AIRFOIL (SHARP) (s102s-il)
Reynolds number: 50,000
Max Cl/Cd: 26.44 at α=9.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s102s-il-50000-n5.txt
Download as CSV file: xf-s102s-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.4104   0.12187   0.11436  -0.0505   1.0000   0.0443
 -12.000  -0.4067   0.11827   0.11080  -0.0508   1.0000   0.0436
 -11.750  -0.4059   0.11433   0.10692  -0.0517   1.0000   0.0428
 -11.500  -0.4075   0.11004   0.10269  -0.0530   1.0000   0.0421
 -11.250  -0.4120   0.10510   0.09782  -0.0548   1.0000   0.0412
 -11.000  -0.4199   0.09933   0.09212  -0.0573   1.0000   0.0402
 -10.750  -0.4343   0.09287   0.08571  -0.0605   1.0000   0.0392
 -10.500  -0.4602   0.08612   0.07898  -0.0639   1.0000   0.0381
 -10.000  -0.5275   0.07636   0.06907  -0.0659   1.0000   0.0365
  -9.750  -0.5465   0.07373   0.06645  -0.0642   1.0000   0.0363
  -9.500  -0.5685   0.07162   0.06436  -0.0614   1.0000   0.0362
  -9.250  -0.5913   0.06996   0.06272  -0.0577   1.0000   0.0361
  -9.000  -0.6112   0.06805   0.06078  -0.0540   1.0000   0.0359
  -8.750  -0.6302   0.06623   0.05890  -0.0503   1.0000   0.0358
  -8.500  -0.6472   0.06438   0.05696  -0.0465   1.0000   0.0357
  -8.250  -0.6571   0.06211   0.05453  -0.0440   0.9987   0.0356
  -8.000  -0.6435   0.05793   0.04993  -0.0463   0.9897   0.0355
  -7.750  -0.6261   0.05420   0.04572  -0.0482   0.9816   0.0354
  -7.500  -0.6067   0.05074   0.04178  -0.0494   0.9736   0.0355
  -7.250  -0.5857   0.04772   0.03827  -0.0501   0.9661   0.0360
  -7.000  -0.5601   0.04499   0.03512  -0.0512   0.9598   0.0371
  -6.750  -0.5361   0.04304   0.03308  -0.0517   0.9533   0.0390
  -6.500  -0.5085   0.04113   0.03088  -0.0523   0.9473   0.0413
  -6.250  -0.4735   0.03919   0.02857  -0.0531   0.9435   0.0432
  -6.000  -0.4458   0.03781   0.02701  -0.0521   0.9375   0.0450
  -5.750  -0.4136   0.03676   0.02599  -0.0520   0.9331   0.0496
  -5.500  -0.3790   0.03586   0.02494  -0.0517   0.9298   0.0552
  -5.250  -0.3604   0.03508   0.02417  -0.0502   0.9230   0.0608
  -5.000  -0.3397   0.03412   0.02319  -0.0494   0.9171   0.0690
  -4.750  -0.3217   0.03309   0.02212  -0.0486   0.9110   0.0799
  -4.500  -0.3093   0.03191   0.02105  -0.0474   0.9036   0.0972
  -4.250  -0.2925   0.02977   0.01940  -0.0481   0.8986   0.1529
  -4.000  -0.3046   0.02944   0.02153  -0.0399   0.8902   0.5436
  -3.750  -0.2853   0.03175   0.02349  -0.0353   0.8852   0.6423
  -3.500  -0.2737   0.03469   0.02640  -0.0255   0.8806   0.6999
  -3.250  -0.2562   0.03643   0.02799  -0.0183   0.8759   0.7389
  -3.000  -0.2330   0.03623   0.02751  -0.0178   0.8715   0.7479
  -2.750  -0.2038   0.03589   0.02687  -0.0188   0.8683   0.7520
  -2.500  -0.1964   0.03559   0.02639  -0.0168   0.8620   0.7568
  -2.250  -0.1774   0.03523   0.02582  -0.0166   0.8570   0.7608
  -2.000  -0.1489   0.03499   0.02535  -0.0175   0.8536   0.7633
  -1.750  -0.1276   0.03480   0.02499  -0.0173   0.8495   0.7661
  -1.500  -0.1152   0.03468   0.02473  -0.0160   0.8441   0.7692
  -1.250  -0.0917   0.03450   0.02438  -0.0165   0.8400   0.7720
  -1.000  -0.0624   0.03431   0.02402  -0.0181   0.8369   0.7746
  -0.750  -0.0448   0.03429   0.02388  -0.0176   0.8323   0.7767
  -0.500  -0.0276   0.03433   0.02383  -0.0168   0.8274   0.7788
  -0.250  -0.0021   0.03432   0.02372  -0.0174   0.8236   0.7809
   0.000   0.0284   0.03430   0.02360  -0.0188   0.8207   0.7826
   0.250   0.0460   0.03445   0.02367  -0.0184   0.8158   0.7847
   0.500   0.0657   0.03461   0.02376  -0.0184   0.8108   0.7873
   0.750   0.0944   0.03471   0.02378  -0.0197   0.8069   0.7895
   1.000   0.1277   0.03479   0.02380  -0.0217   0.8039   0.7913
   1.250   0.1411   0.03513   0.02412  -0.0205   0.7975   0.7930
   1.500   0.1654   0.03535   0.02433  -0.0209   0.7926   0.7948
   1.750   0.1972   0.03549   0.02446  -0.0223   0.7888   0.7969
   2.000   0.2166   0.03585   0.02482  -0.0221   0.7827   0.7994
   2.250   0.2407   0.03615   0.02513  -0.0225   0.7766   0.8019
   2.500   0.2760   0.03628   0.02527  -0.0244   0.7723   0.8040
   2.750   0.2944   0.03674   0.02576  -0.0243   0.7642   0.8064
   3.000   0.3257   0.03688   0.02595  -0.0254   0.7580   0.8083
   3.250   0.3499   0.03712   0.02627  -0.0254   0.7498   0.8105
   3.500   0.3855   0.03692   0.02614  -0.0265   0.7409   0.8130
   3.750   0.4178   0.03646   0.02575  -0.0267   0.7266   0.8158
   4.000   0.4589   0.03540   0.02475  -0.0273   0.7105   0.8186
   4.250   0.4996   0.03424   0.02369  -0.0279   0.6943   0.8214
   4.500   0.5311   0.03356   0.02310  -0.0276   0.6794   0.8241
   4.750   0.5596   0.03300   0.02266  -0.0270   0.6649   0.8270
   5.000   0.5875   0.03245   0.02226  -0.0264   0.6499   0.8301
   5.250   0.6139   0.03194   0.02189  -0.0256   0.6334   0.8338
   5.500   0.6397   0.03140   0.02148  -0.0248   0.6146   0.8380
   5.750   0.6595   0.03097   0.02122  -0.0230   0.5938   0.8423
   6.000   0.6680   0.03119   0.02161  -0.0205   0.5653   0.8477
   6.500   0.6987   0.03099   0.02165  -0.0167   0.4783   0.8591
   6.750   0.7473   0.02890   0.01894  -0.0160   0.3976   0.8639
   7.000   0.7628   0.02958   0.01911  -0.0142   0.3440   0.8701
   7.250   0.7738   0.03058   0.01988  -0.0124   0.3123   0.8775
   7.500   0.7877   0.03158   0.02074  -0.0112   0.2897   0.8862
   7.750   0.8033   0.03248   0.02156  -0.0101   0.2725   0.8970
   8.000   0.8220   0.03330   0.02237  -0.0095   0.2577   0.9109
   8.250   0.8455   0.03408   0.02319  -0.0096   0.2450   0.9316
   8.500   0.8724   0.03471   0.02382  -0.0101   0.2350   1.0000
   8.750   0.9048   0.03560   0.02475  -0.0115   0.2249   1.0000
   9.000   0.9387   0.03653   0.02576  -0.0131   0.2157   1.0000
   9.250   0.9772   0.03743   0.02662  -0.0151   0.2071   1.0000
   9.500   1.0123   0.03854   0.02795  -0.0168   0.1999   1.0000
   9.750   1.0492   0.03968   0.02913  -0.0187   0.1928   1.0000
  10.000   1.0790   0.04106   0.03070  -0.0198   0.1862   1.0000
  10.250   1.1079   0.04248   0.03229  -0.0209   0.1803   1.0000
  10.500   1.1426   0.04399   0.03383  -0.0227   0.1747   1.0000
  10.750   1.1563   0.04574   0.03594  -0.0219   0.1694   1.0000
  11.000   1.1772   0.04735   0.03770  -0.0220   0.1642   1.0000
  11.250   1.2030   0.04909   0.03951  -0.0227   0.1594   1.0000
  11.500   1.2050   0.05123   0.04206  -0.0207   0.1553   1.0000
  11.750   1.2135   0.05317   0.04423  -0.0196   0.1507   1.0000
  12.000   1.2392   0.05477   0.04581  -0.0202   0.1460   1.0000
  12.250   1.2301   0.05748   0.04891  -0.0176   0.1429   1.0000
  12.500   1.2199   0.06036   0.05212  -0.0155   0.1396   1.0000
  12.750   1.2151   0.06306   0.05506  -0.0140   0.1361   1.0000
  13.000   1.2325   0.06467   0.05669  -0.0138   0.1319   1.0000
  13.250   1.2181   0.06826   0.06055  -0.0124   0.1296   1.0000
  13.500   1.1870   0.07325   0.06589  -0.0113   0.1281   1.0000
  13.750   1.1515   0.07935   0.07228  -0.0115   0.1270   1.0000
  14.000   1.1058   0.08748   0.08067  -0.0133   0.1267   1.0000
  14.250   1.0367   0.10056   0.09393  -0.0190   0.1274   1.0000
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