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SOMERS S102 AIRFOIL (SHARP) (s102s-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: SOMERS S102 AIRFOIL (SHARP) (s102s-il)
Reynolds number: 1,000,000
Max Cl/Cd: 95.95 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s102s-il-1000000.txt
Download as CSV file: xf-s102s-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4414   0.09572   0.09408  -0.0525   1.0000   0.0106
 -11.500  -0.4545   0.08840   0.08679  -0.0557   1.0000   0.0106
 -11.250  -0.5068   0.07140   0.06967  -0.0656   1.0000   0.0105
  -8.250  -0.4875   0.01942   0.01431  -0.0847   0.8575   0.0077
  -8.000  -0.4661   0.01832   0.01307  -0.0838   0.8385   0.0075
  -7.750  -0.4459   0.01693   0.01151  -0.0827   0.8231   0.0073
  -7.500  -0.4255   0.01589   0.01033  -0.0817   0.8098   0.0072
  -7.250  -0.4054   0.01504   0.00936  -0.0806   0.7983   0.0071
  -6.750  -0.3645   0.01365   0.00778  -0.0787   0.7786   0.0071
  -6.500  -0.3435   0.01306   0.00710  -0.0778   0.7704   0.0071
  -6.250  -0.3212   0.01251   0.00648  -0.0773   0.7629   0.0072
  -6.000  -0.2983   0.01204   0.00593  -0.0767   0.7559   0.0072
  -5.750  -0.2742   0.01158   0.00542  -0.0764   0.7498   0.0074
  -5.500  -0.2492   0.01121   0.00499  -0.0762   0.7440   0.0076
  -5.250  -0.2254   0.01069   0.00439  -0.0758   0.7386   0.0082
  -5.000  -0.1990   0.01037   0.00405  -0.0758   0.7342   0.0092
  -4.750  -0.1723   0.01008   0.00372  -0.0758   0.7297   0.0105
  -4.500  -0.1457   0.00979   0.00340  -0.0758   0.7254   0.0139
  -4.250  -0.1191   0.00944   0.00310  -0.0759   0.7215   0.0289
  -4.000  -0.0920   0.00911   0.00288  -0.0761   0.7180   0.0541
  -3.750  -0.0653   0.00865   0.00262  -0.0764   0.7145   0.1090
  -3.500  -0.0415   0.00739   0.00208  -0.0770   0.7110   0.3114
  -3.250  -0.0164   0.00636   0.00181  -0.0775   0.7074   0.5538
  -3.000   0.0130   0.00648   0.00194  -0.0778   0.7045   0.5733
  -2.750   0.0426   0.00664   0.00205  -0.0781   0.7017   0.5843
  -2.500   0.0717   0.00674   0.00217  -0.0782   0.6990   0.5929
  -2.250   0.1008   0.00694   0.00234  -0.0783   0.6964   0.6033
  -2.000   0.1297   0.00717   0.00258  -0.0784   0.6938   0.6113
  -1.750   0.1590   0.00720   0.00254  -0.0788   0.6912   0.6123
  -1.500   0.1884   0.00719   0.00250  -0.0791   0.6889   0.6130
  -1.250   0.2176   0.00715   0.00244  -0.0795   0.6855   0.6136
  -1.000   0.2466   0.00713   0.00238  -0.0797   0.6806   0.6142
  -0.750   0.2753   0.00716   0.00234  -0.0800   0.6752   0.6147
  -0.500   0.3043   0.00714   0.00230  -0.0803   0.6704   0.6153
  -0.250   0.3333   0.00713   0.00226  -0.0805   0.6654   0.6158
   0.000   0.3619   0.00712   0.00221  -0.0807   0.6605   0.6166
   0.250   0.3906   0.00708   0.00215  -0.0810   0.6552   0.6175
   0.500   0.4192   0.00703   0.00211  -0.0812   0.6488   0.6183
   0.750   0.4475   0.00706   0.00209  -0.0813   0.6426   0.6191
   1.000   0.4763   0.00702   0.00207  -0.0816   0.6369   0.6198
   1.250   0.5048   0.00703   0.00206  -0.0818   0.6305   0.6206
   1.500   0.5332   0.00705   0.00208  -0.0819   0.6244   0.6213
   1.750   0.5618   0.00705   0.00208  -0.0821   0.6171   0.6221
   2.000   0.5898   0.00709   0.00210  -0.0822   0.6096   0.6229
   2.250   0.6183   0.00710   0.00212  -0.0824   0.6011   0.6238
   2.500   0.6462   0.00714   0.00215  -0.0825   0.5911   0.6247
   2.750   0.6737   0.00720   0.00218  -0.0825   0.5771   0.6257
   3.000   0.7004   0.00730   0.00222  -0.0824   0.5529   0.6267
   3.250   0.7206   0.00778   0.00237  -0.0811   0.4745   0.6277
   3.500   0.7345   0.00877   0.00283  -0.0788   0.3609   0.6285
   3.750   0.7526   0.00948   0.00318  -0.0773   0.2862   0.6294
   4.000   0.7733   0.00999   0.00346  -0.0763   0.2383   0.6302
   4.500   0.8192   0.01068   0.00391  -0.0749   0.1867   0.6317
   4.750   0.8430   0.01095   0.00411  -0.0743   0.1718   0.6324
   5.000   0.8665   0.01120   0.00431  -0.0737   0.1603   0.6338
   5.250   0.8911   0.01138   0.00449  -0.0733   0.1536   0.6351
   5.500   0.9142   0.01164   0.00472  -0.0726   0.1454   0.6363
   5.750   0.9390   0.01181   0.00492  -0.0722   0.1418   0.6375
   6.000   0.9626   0.01203   0.00514  -0.0716   0.1375   0.6387
   6.250   0.9850   0.01232   0.00541  -0.0708   0.1324   0.6400
   6.500   1.0085   0.01253   0.00565  -0.0701   0.1298   0.6412
   6.750   1.0321   0.01271   0.00587  -0.0695   0.1272   0.6426
   7.000   1.0546   0.01295   0.00611  -0.0688   0.1243   0.6439
   7.250   1.0760   0.01323   0.00639  -0.0678   0.1210   0.6454
   7.500   1.0933   0.01359   0.00676  -0.0660   0.1169   0.6468
   7.750   1.1140   0.01378   0.00699  -0.0649   0.1158   0.6480
   8.000   1.1347   0.01397   0.00723  -0.0638   0.1140   0.6497
   8.250   1.1547   0.01420   0.00751  -0.0626   0.1119   0.6516
   8.500   1.1739   0.01449   0.00783  -0.0613   0.1095   0.6535
   8.750   1.1916   0.01485   0.00820  -0.0597   0.1064   0.6553
   9.000   1.2067   0.01535   0.00872  -0.0578   0.1031   0.6572
   9.250   1.2276   0.01558   0.00902  -0.0569   0.1020   0.6592
   9.500   1.2479   0.01585   0.00934  -0.0559   0.1003   0.6612
   9.750   1.2673   0.01616   0.00968  -0.0548   0.0978   0.6631
  10.000   1.2854   0.01654   0.01007  -0.0535   0.0950   0.6651
  10.250   1.3003   0.01707   0.01063  -0.0518   0.0915   0.6680
  10.500   1.3189   0.01744   0.01106  -0.0507   0.0896   0.6708
  10.750   1.3385   0.01776   0.01144  -0.0498   0.0871   0.6736
  11.000   1.3561   0.01819   0.01188  -0.0486   0.0833   0.6767
  11.250   1.3702   0.01884   0.01252  -0.0471   0.0789   0.6796
  11.500   1.3884   0.01926   0.01303  -0.0461   0.0773   0.6833
  11.750   1.4049   0.01978   0.01360  -0.0449   0.0741   0.6875
  12.000   1.4186   0.02050   0.01431  -0.0435   0.0684   0.6921
  12.250   1.4343   0.02112   0.01497  -0.0423   0.0647   0.6967
  12.500   1.4461   0.02199   0.01583  -0.0409   0.0584   0.7025
  12.750   1.4601   0.02276   0.01666  -0.0397   0.0550   0.7089
  13.000   1.4704   0.02380   0.01770  -0.0382   0.0489   0.7158
  13.250   1.4819   0.02478   0.01873  -0.0369   0.0449   0.7244
  13.500   1.4917   0.02591   0.01989  -0.0355   0.0401   0.7344
  13.750   1.5007   0.02714   0.02116  -0.0342   0.0359   0.7473
  14.000   1.5108   0.02829   0.02240  -0.0330   0.0326   0.7645
  14.250   1.5179   0.02970   0.02388  -0.0317   0.0287   0.7896
  14.500   1.5265   0.03087   0.02524  -0.0304   0.0260   0.8403
  14.750   1.5317   0.03214   0.02677  -0.0289   0.0232   1.0000
  15.000   1.5402   0.03361   0.02828  -0.0280   0.0210   1.0000
  15.250   1.5462   0.03534   0.03003  -0.0271   0.0187   1.0000
  15.500   1.5533   0.03699   0.03174  -0.0263   0.0171   1.0000
  15.750   1.5574   0.03897   0.03375  -0.0254   0.0153   1.0000
  16.000   1.5639   0.04078   0.03563  -0.0248   0.0140   1.0000
  16.250   1.5675   0.04291   0.03780  -0.0242   0.0128   1.0000
  16.500   1.5709   0.04511   0.04009  -0.0237   0.0118   1.0000
  16.750   1.5745   0.04736   0.04240  -0.0234   0.0109   1.0000
  17.000   1.5755   0.04994   0.04506  -0.0231   0.0102   1.0000
  17.250   1.5754   0.05274   0.04794  -0.0230   0.0094   1.0000
  17.500   1.5771   0.05541   0.05069  -0.0230   0.0089   1.0000
  17.750   1.5763   0.05845   0.05382  -0.0232   0.0084   1.0000
  18.000   1.5737   0.06183   0.05729  -0.0236   0.0080   1.0000
  18.250   1.5679   0.06575   0.06131  -0.0243   0.0075   1.0000
  18.500   1.5636   0.06959   0.06526  -0.0252   0.0071   1.0000
  18.750   1.5578   0.07379   0.06958  -0.0264   0.0069   1.0000
  19.000   1.5503   0.07843   0.07433  -0.0279   0.0066   1.0000
  19.250   1.5397   0.08372   0.07975  -0.0299   0.0064   1.0000
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