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SOMERS S102 AIRFOIL (BLUNT) (s102b-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SOMERS S102 AIRFOIL (BLUNT) (s102b-il)
Reynolds number: 100,000
Max Cl/Cd: 42.63 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s102b-il-100000.txt
Download as CSV file: xf-s102b-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SOMERS S102 AIRFOIL (BLUNT)                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4189   0.10861   0.10376  -0.0411   1.0000   0.1194
 -10.250  -0.4794   0.10072   0.09603  -0.0540   1.0000   0.1231
 -10.000  -0.5220   0.09596   0.09132  -0.0586   1.0000   0.1234
  -9.500  -0.4964   0.08872   0.08422  -0.0563   1.0000   0.1379
  -9.250  -0.5374   0.08590   0.08150  -0.0556   1.0000   0.1380
  -9.000  -0.5735   0.08438   0.08009  -0.0520   1.0000   0.1380
  -8.750  -0.6081   0.08348   0.07925  -0.0472   1.0000   0.1380
  -8.500  -0.6428   0.08266   0.07845  -0.0427   1.0000   0.1381
  -8.250  -0.6797   0.08185   0.07754  -0.0392   1.0000   0.1384
  -7.250  -0.6010   0.06368   0.05954  -0.0479   0.9814   0.1916
  -6.750  -0.5540   0.04503   0.03801  -0.0569   0.9654   0.0657
  -6.500  -0.5234   0.04059   0.03287  -0.0576   0.9603   0.0547
  -6.250  -0.4888   0.03708   0.02902  -0.0595   0.9568   0.0518
  -6.000  -0.4584   0.03480   0.02639  -0.0603   0.9521   0.0516
  -5.750  -0.4299   0.03308   0.02438  -0.0606   0.9467   0.0530
  -5.500  -0.3954   0.03135   0.02240  -0.0616   0.9432   0.0543
  -5.250  -0.3579   0.02975   0.02059  -0.0628   0.9407   0.0555
  -5.000  -0.3349   0.02836   0.01925  -0.0616   0.9360   0.0577
  -4.750  -0.3105   0.02740   0.01841  -0.0613   0.9310   0.0640
  -4.500  -0.2806   0.02622   0.01738  -0.0618   0.9273   0.0737
  -4.250  -0.2462   0.02496   0.01626  -0.0636   0.9245   0.0975
  -4.000  -0.2364   0.02335   0.01727  -0.0618   0.9186   0.6039
  -3.750  -0.2347   0.02679   0.02080  -0.0511   0.9130   0.6584
  -3.500  -0.2224   0.02919   0.02318  -0.0431   0.9095   0.6941
  -3.250  -0.2211   0.03072   0.02470  -0.0345   0.9043   0.7188
  -3.000  -0.2203   0.03207   0.02603  -0.0256   0.8995   0.7485
  -2.750  -0.2104   0.03339   0.02732  -0.0166   0.8968   0.7849
  -2.500  -0.1882   0.03366   0.02744  -0.0146   0.8941   0.8071
  -2.250  -0.1582   0.03337   0.02696  -0.0157   0.8915   0.8108
  -2.000  -0.1615   0.03318   0.02672  -0.0119   0.8856   0.8138
  -1.750  -0.1432   0.03299   0.02640  -0.0119   0.8822   0.8165
  -1.500  -0.1157   0.03280   0.02608  -0.0136   0.8792   0.8187
  -1.250  -0.0798   0.03266   0.02578  -0.0167   0.8766   0.8204
  -1.000  -0.0707   0.03269   0.02573  -0.0159   0.8725   0.8221
  -0.750  -0.0492   0.03271   0.02566  -0.0170   0.8686   0.8233
  -0.500  -0.0223   0.03269   0.02555  -0.0182   0.8652   0.8243
  -0.250   0.0099   0.03270   0.02548  -0.0202   0.8624   0.8255
   0.000   0.0417   0.03281   0.02551  -0.0224   0.8594   0.8261
   0.250   0.0548   0.03306   0.02573  -0.0219   0.8547   0.8274
   0.500   0.0815   0.03324   0.02586  -0.0232   0.8504   0.8286
   0.750   0.1175   0.03338   0.02596  -0.0260   0.8469   0.8292
   1.000   0.1501   0.03363   0.02617  -0.0282   0.8429   0.8299
   1.250   0.1673   0.03401   0.02655  -0.0283   0.8368   0.8313
   1.500   0.2024   0.03421   0.02673  -0.0308   0.8319   0.8325
   1.750   0.2417   0.03441   0.02691  -0.0337   0.8272   0.8333
   2.000   0.2605   0.03484   0.02736  -0.0341   0.8190   0.8342
   2.250   0.3095   0.03472   0.02724  -0.0379   0.8133   0.8351
   2.500   0.3515   0.03409   0.02662  -0.0398   0.7982   0.8364
   2.750   0.4320   0.03157   0.02410  -0.0447   0.7809   0.8376
   3.000   0.4701   0.03074   0.02330  -0.0458   0.7672   0.8388
   3.250   0.5007   0.03038   0.02300  -0.0461   0.7574   0.8398
   3.500   0.5480   0.02912   0.02179  -0.0477   0.7504   0.8410
   3.750   0.5758   0.02880   0.02156  -0.0476   0.7394   0.8424
   4.000   0.6269   0.02713   0.01993  -0.0493   0.7329   0.8437
   4.250   0.6543   0.02668   0.01959  -0.0489   0.7203   0.8458
   4.500   0.6884   0.02582   0.01881  -0.0491   0.7085   0.8481
   4.750   0.7280   0.02456   0.01761  -0.0496   0.6959   0.8503
   5.000   0.7633   0.02345   0.01659  -0.0497   0.6794   0.8524
   5.250   0.7957   0.02240   0.01561  -0.0495   0.6586   0.8544
   5.500   0.8234   0.02127   0.01457  -0.0481   0.6318   0.8565
   5.750   0.8426   0.02037   0.01376  -0.0455   0.5816   0.8591
   6.000   0.8530   0.02001   0.01246  -0.0411   0.4202   0.8619
   6.250   0.8565   0.02157   0.01320  -0.0378   0.3373   0.8650
   6.500   0.8733   0.02271   0.01398  -0.0368   0.3020   0.8686
   6.750   0.8935   0.02358   0.01461  -0.0360   0.2817   0.8721
   7.000   0.9172   0.02436   0.01526  -0.0357   0.2662   0.8760
   7.250   0.9436   0.02516   0.01599  -0.0360   0.2532   0.8801
   7.500   0.9729   0.02604   0.01684  -0.0369   0.2426   0.8843
   7.750   1.0010   0.02689   0.01759  -0.0373   0.2343   0.8885
   8.000   1.0276   0.02771   0.01854  -0.0376   0.2266   0.8937
   8.250   1.0583   0.02869   0.01945  -0.0387   0.2190   0.8994
   8.500   1.0829   0.02958   0.02051  -0.0385   0.2129   0.9057
   8.750   1.1093   0.03051   0.02155  -0.0388   0.2068   0.9137
   9.000   1.1372   0.03171   0.02271  -0.0392   0.2011   0.9229
   9.250   1.1563   0.03254   0.02388  -0.0382   0.1957   0.9352
   9.500   1.1807   0.03353   0.02501  -0.0382   0.1903   0.9528
   9.750   1.2123   0.03510   0.02670  -0.0400   0.1846   1.0000
  10.000   1.2388   0.03657   0.02847  -0.0412   0.1786   1.0000
  10.250   1.2717   0.03822   0.03011  -0.0434   0.1727   1.0000
  10.500   1.2929   0.04018   0.03243  -0.0440   0.1673   1.0000
  10.750   1.3168   0.04180   0.03427  -0.0447   0.1614   1.0000
  11.000   1.3453   0.04396   0.03638  -0.0464   0.1556   1.0000
  11.250   1.3519   0.04588   0.03880  -0.0446   0.1506   1.0000
  11.500   1.3735   0.04733   0.04029  -0.0449   0.1447   1.0000
  11.750   1.3873   0.04973   0.04284  -0.0443   0.1398   1.0000
  12.000   1.3832   0.05205   0.04560  -0.0413   0.1355   1.0000
  12.250   1.4029   0.05315   0.04668  -0.0411   0.1297   1.0000
  12.500   1.4071   0.05577   0.04946  -0.0395   0.1255   1.0000
  12.750   1.3860   0.05851   0.05262  -0.0349   0.1230   1.0000
  13.000   1.3700   0.06120   0.05558  -0.0314   0.1201   1.0000
  13.250   1.4128   0.06155   0.05560  -0.0333   0.1127   1.0000
  13.500   1.3811   0.06493   0.05938  -0.0290   0.1117   1.0000
  13.750   1.3481   0.06920   0.06400  -0.0259   0.1107   1.0000
  14.000   1.3127   0.07438   0.06949  -0.0241   0.1102   1.0000
  14.250   1.2733   0.08073   0.07612  -0.0237   0.1101   1.0000
  14.500   1.2296   0.08848   0.08411  -0.0247   0.1107   1.0000
  14.750   1.1825   0.09786   0.09367  -0.0276   0.1116   1.0000
  15.000   1.1336   0.10917   0.10508  -0.0324   0.1125   1.0000
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