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SOMERS S102 AIRFOIL (SHARP) (s102s-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SOMERS S102 AIRFOIL (SHARP) (s102s-il)
Reynolds number: 100,000
Max Cl/Cd: 40.53 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s102s-il-100000.txt
Download as CSV file: xf-s102s-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3850   0.11267   0.10767  -0.0467   1.0000   0.1115
 -10.750  -0.3918   0.10922   0.10430  -0.0481   1.0000   0.1172
 -10.500  -0.4492   0.10314   0.09842  -0.0569   1.0000   0.1200
 -10.250  -0.4016   0.10168   0.09691  -0.0493   1.0000   0.1244
 -10.000  -0.4004   0.09888   0.09416  -0.0487   1.0000   0.1296
  -9.750  -0.4550   0.09287   0.08835  -0.0551   1.0000   0.1346
  -9.500  -0.4291   0.09089   0.08639  -0.0504   1.0000   0.1395
  -9.250  -0.4321   0.08840   0.08398  -0.0491   1.0000   0.1451
  -9.000  -0.4756   0.08388   0.07961  -0.0506   1.0000   0.1480
  -8.750  -0.4090   0.08844   0.08476  -0.0317   1.0000   0.1595
  -8.500  -0.4517   0.08044   0.07682  -0.0385   0.9963   0.1645
  -8.250  -0.6822   0.08222   0.07777  -0.0416   0.9944   0.1355
  -8.000  -0.6235   0.07747   0.07358  -0.0368   0.9984   0.1462
  -7.750  -0.6204   0.07220   0.06821  -0.0421   0.9898   0.1564
  -6.750  -0.5672   0.04726   0.04069  -0.0552   0.9584   0.0739
  -6.500  -0.5488   0.04324   0.03542  -0.0527   0.9510   0.0542
  -6.250  -0.5202   0.04051   0.03236  -0.0536   0.9467   0.0538
  -6.000  -0.4871   0.03758   0.02915  -0.0551   0.9439   0.0534
  -5.750  -0.4681   0.03561   0.02694  -0.0538   0.9380   0.0531
  -5.500  -0.4389   0.03350   0.02461  -0.0539   0.9338   0.0528
  -5.250  -0.4039   0.03179   0.02268  -0.0547   0.9307   0.0532
  -5.000  -0.3701   0.03004   0.02092  -0.0553   0.9281   0.0554
  -4.750  -0.3573   0.02927   0.02024  -0.0530   0.9224   0.0588
  -4.500  -0.3317   0.02862   0.01951  -0.0526   0.9185   0.0650
  -4.250  -0.3057   0.02738   0.01851  -0.0525   0.9155   0.0746
  -4.000  -0.2863   0.02661   0.01781  -0.0514   0.9113   0.0912
  -3.750  -0.2735   0.02506   0.01669  -0.0502   0.9061   0.1439
  -3.500  -0.2765   0.02706   0.02106  -0.0402   0.9015   0.6534
  -3.250  -0.2631   0.02967   0.02366  -0.0325   0.8986   0.6956
  -3.000  -0.2688   0.03090   0.02490  -0.0242   0.8935   0.7150
  -2.750  -0.2642   0.03223   0.02619  -0.0169   0.8892   0.7441
  -2.500  -0.2598   0.03372   0.02769  -0.0073   0.8865   0.7773
  -2.250  -0.2417   0.03462   0.02850  -0.0023   0.8843   0.8066
  -2.000  -0.2240   0.03460   0.02835  -0.0003   0.8813   0.8137
  -1.750  -0.2228   0.03425   0.02791   0.0024   0.8769   0.8169
  -1.500  -0.2085   0.03398   0.02751   0.0027   0.8739   0.8194
  -1.250  -0.1827   0.03375   0.02713   0.0011   0.8707   0.8212
  -1.000  -0.1497   0.03364   0.02686  -0.0015   0.8682   0.8227
  -0.750  -0.1377   0.03355   0.02668  -0.0004   0.8650   0.8240
  -0.500  -0.1241   0.03349   0.02655   0.0004   0.8612   0.8255
  -0.250  -0.1012   0.03349   0.02646  -0.0003   0.8579   0.8266
   0.000  -0.0699   0.03355   0.02642  -0.0023   0.8546   0.8274
   0.250  -0.0309   0.03371   0.02648  -0.0054   0.8517   0.8285
   0.500  -0.0230   0.03383   0.02656  -0.0041   0.8471   0.8296
   0.750   0.0010   0.03398   0.02666  -0.0051   0.8424   0.8303
   1.000   0.0359   0.03417   0.02679  -0.0075   0.8382   0.8316
   1.250   0.0678   0.03445   0.02702  -0.0095   0.8338   0.8328
   1.500   0.0846   0.03470   0.02725  -0.0096   0.8275   0.8337
   1.750   0.1229   0.03491   0.02742  -0.0124   0.8221   0.8344
   2.000   0.1499   0.03524   0.02773  -0.0137   0.8155   0.8355
   2.250   0.1798   0.03547   0.02795  -0.0153   0.8079   0.8369
   2.500   0.2185   0.03566   0.02814  -0.0178   0.8004   0.8382
   2.750   0.2658   0.03521   0.02770  -0.0206   0.7885   0.8391
   3.000   0.3378   0.03343   0.02592  -0.0250   0.7711   0.8397
   3.250   0.3880   0.03203   0.02456  -0.0270   0.7559   0.8407
   3.500   0.4102   0.03198   0.02456  -0.0265   0.7435   0.8422
   3.750   0.4880   0.02992   0.02258  -0.0321   0.7394   0.8432
   4.000   0.5073   0.02982   0.02256  -0.0309   0.7268   0.8454
   4.250   0.5887   0.02747   0.02028  -0.0369   0.7228   0.8470
   4.500   0.6150   0.02701   0.01993  -0.0364   0.7097   0.8493
   4.750   0.6550   0.02595   0.01895  -0.0374   0.6972   0.8511
   5.000   0.7021   0.02451   0.01761  -0.0392   0.6836   0.8529
   5.250   0.7411   0.02322   0.01641  -0.0396   0.6672   0.8548
   5.500   0.7773   0.02183   0.01509  -0.0394   0.6454   0.8570
   5.750   0.8001   0.02075   0.01411  -0.0373   0.6131   0.8596
   6.000   0.8075   0.02007   0.01347  -0.0330   0.5533   0.8632
   6.250   0.8134   0.02007   0.01233  -0.0281   0.3963   0.8670
   6.500   0.8134   0.02130   0.01294  -0.0240   0.3352   0.8708
   6.750   0.8261   0.02225   0.01357  -0.0220   0.3037   0.8747
   7.000   0.8489   0.02313   0.01421  -0.0218   0.2819   0.8786
   7.250   0.8773   0.02399   0.01492  -0.0226   0.2653   0.8828
   7.500   0.9078   0.02486   0.01566  -0.0236   0.2524   0.8869
   7.750   0.9358   0.02559   0.01644  -0.0240   0.2424   0.8919
   8.000   0.9679   0.02654   0.01737  -0.0254   0.2334   0.8974
   8.250   0.9960   0.02734   0.01819  -0.0259   0.2252   0.9035
   8.500   1.0259   0.02833   0.01924  -0.0267   0.2183   0.9113
   8.750   1.0516   0.02916   0.02021  -0.0268   0.2119   0.9205
   9.000   1.0853   0.03042   0.02141  -0.0283   0.2056   0.9310
   9.250   1.1073   0.03126   0.02258  -0.0279   0.1998   0.9474
   9.500   1.1437   0.03251   0.02392  -0.0305   0.1935   0.9810
   9.750   1.1752   0.03414   0.02575  -0.0324   0.1877   1.0000
  10.000   1.2027   0.03555   0.02737  -0.0338   0.1816   1.0000
  10.250   1.2407   0.03761   0.02931  -0.0369   0.1756   1.0000
  10.500   1.2556   0.03904   0.03120  -0.0362   0.1705   1.0000
  10.750   1.2805   0.04058   0.03289  -0.0371   0.1647   1.0000
  11.000   1.3065   0.04271   0.03506  -0.0382   0.1592   1.0000
  11.250   1.3132   0.04447   0.03723  -0.0363   0.1543   1.0000
  11.500   1.3352   0.04590   0.03870  -0.0365   0.1486   1.0000
  11.750   1.3480   0.04823   0.04118  -0.0358   0.1438   1.0000
  12.000   1.3432   0.05034   0.04370  -0.0325   0.1398   1.0000
  12.250   1.3601   0.05160   0.04500  -0.0319   0.1342   1.0000
  12.500   1.3696   0.05399   0.04747  -0.0308   0.1297   1.0000
  12.750   1.3477   0.05640   0.05026  -0.0258   0.1274   1.0000
  13.000   1.3296   0.05904   0.05320  -0.0220   0.1247   1.0000
  13.250   1.3787   0.05962   0.05344  -0.0248   0.1167   1.0000
  13.500   1.3469   0.06255   0.05674  -0.0200   0.1156   1.0000
  13.750   1.3149   0.06641   0.06095  -0.0166   0.1147   1.0000
  14.000   1.2804   0.07113   0.06598  -0.0145   0.1140   1.0000
  14.250   1.2420   0.07698   0.07211  -0.0136   0.1138   1.0000
  14.500   1.1991   0.08419   0.07956  -0.0143   0.1142   1.0000
  14.750   1.1518   0.09318   0.08875  -0.0168   0.1151   1.0000
  15.000   1.1019   0.10418   0.09988  -0.0214   0.1161   1.0000
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