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S1210 12% (s1210-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S1210 12% (s1210-il)
Reynolds number: 500,000
Max Cl/Cd: 121.45 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1210-il-500000.txt
Download as CSV file: xf-s1210-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1210 12%                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.0055   0.09232   0.09018  -0.0753   0.9706   0.0202
  -9.000  -0.0093   0.08699   0.08485  -0.0790   0.9653   0.0209
  -8.750   0.0011   0.08235   0.08022  -0.0813   0.9624   0.0212
  -8.500   0.0205   0.07945   0.07732  -0.0830   0.9606   0.0216
  -8.250   0.0347   0.07709   0.07497  -0.0837   0.9558   0.0226
  -8.000   0.0455   0.07355   0.07143  -0.0856   0.9509   0.0234
  -7.750   0.0500   0.06741   0.06530  -0.0914   0.9479   0.0255
  -7.500   0.0496   0.06288   0.06079  -0.0936   0.9387   0.0257
  -7.250   0.0625   0.05892   0.05684  -0.0949   0.9349   0.0263
  -7.000   0.0706   0.05652   0.05444  -0.0947   0.9244   0.0267
  -6.750   0.0870   0.05368   0.05160  -0.0966   0.9177   0.0276
  -6.500   0.0994   0.04998   0.04788  -0.0994   0.9077   0.0288
  -6.250   0.0964   0.04233   0.04021  -0.1073   0.8943   0.0314
  -6.000   0.1134   0.03601   0.03386  -0.1143   0.8825   0.0324
  -5.750   0.1516   0.03308   0.03086  -0.1209   0.8689   0.0335
  -5.500   0.1836   0.02700   0.02468  -0.1329   0.8510   0.0365
  -5.250   0.2829   0.00953   0.00632  -0.1927   0.8517   0.0419
  -5.000   0.3410   0.01622   0.01189  -0.2121   0.8790   0.0276
  -4.750   0.4201   0.01284   0.00787  -0.2234   0.8650   0.0223
  -4.500   0.4898   0.01167   0.00644  -0.2324   0.8402   0.0225
  -4.250   0.5426   0.01114   0.00566  -0.2378   0.8061   0.0232
  -4.000   0.5807   0.01088   0.00515  -0.2400   0.7712   0.0238
  -3.750   0.6137   0.01075   0.00479  -0.2411   0.7400   0.0248
  -3.250   0.6808   0.01041   0.00404  -0.2436   0.6884   0.0273
  -3.000   0.7126   0.01034   0.00380  -0.2444   0.6674   0.0294
  -2.750   0.7442   0.01030   0.00357  -0.2451   0.6488   0.0333
  -2.500   0.7889   0.00966   0.00333  -0.2494   0.6314   0.2134
  -2.250   0.8165   0.00983   0.00344  -0.2492   0.6169   0.2472
  -2.000   0.8437   0.01003   0.00355  -0.2488   0.6043   0.2654
  -1.750   0.8710   0.01024   0.00367  -0.2485   0.5931   0.2795
  -1.500   0.8989   0.01040   0.00375  -0.2484   0.5826   0.2896
  -1.250   0.9267   0.01056   0.00385  -0.2482   0.5734   0.2984
  -1.000   0.9548   0.01071   0.00392  -0.2481   0.5645   0.3068
  -0.750   0.9833   0.01081   0.00398  -0.2481   0.5564   0.3120
  -0.500   1.0117   0.01094   0.00402  -0.2480   0.5489   0.3158
  -0.250   1.0402   0.01105   0.00407  -0.2480   0.5424   0.3193
   0.000   1.0694   0.01111   0.00413  -0.2482   0.5358   0.3242
   0.250   1.0978   0.01128   0.00424  -0.2482   0.5298   0.3294
   0.500   1.1264   0.01135   0.00431  -0.2482   0.5242   0.3345
   0.750   1.1553   0.01145   0.00440  -0.2483   0.5188   0.3402
   1.000   1.1838   0.01163   0.00453  -0.2484   0.5137   0.3467
   1.250   1.2123   0.01172   0.00464  -0.2484   0.5090   0.3538
   1.500   1.2411   0.01181   0.00477  -0.2485   0.5041   0.3622
   1.750   1.2690   0.01198   0.00490  -0.2484   0.4986   0.3717
   2.000   1.2972   0.01209   0.00505  -0.2484   0.4928   0.3831
   2.250   1.3253   0.01219   0.00518  -0.2484   0.4870   0.3961
   2.500   1.3534   0.01236   0.00535  -0.2483   0.4824   0.4108
   2.750   1.3818   0.01251   0.00554  -0.2484   0.4782   0.4277
   3.000   1.4099   0.01260   0.00572  -0.2484   0.4736   0.4472
   3.500   1.4652   0.01293   0.00611  -0.2482   0.4626   0.4939
   3.750   1.4928   0.01301   0.00630  -0.2481   0.4574   0.5220
   4.000   1.5200   0.01315   0.00650  -0.2479   0.4514   0.5542
   4.250   1.5473   0.01332   0.00674  -0.2478   0.4455   0.5913
   4.750   1.6017   0.01358   0.00722  -0.2474   0.4342   0.6817
   5.000   1.6287   0.01372   0.00750  -0.2472   0.4289   0.7408
   5.250   1.6542   0.01377   0.00774  -0.2466   0.4236   0.8241
   5.500   1.6687   0.01374   0.00784  -0.2436   0.4185   1.0000
   5.750   1.6943   0.01398   0.00807  -0.2431   0.4124   1.0000
   6.000   1.7198   0.01417   0.00829  -0.2426   0.4052   1.0000
   6.250   1.7441   0.01446   0.00856  -0.2418   0.3984   1.0000
   6.500   1.7695   0.01464   0.00879  -0.2413   0.3907   1.0000
   6.750   1.7929   0.01495   0.00908  -0.2404   0.3825   1.0000
   7.000   1.8173   0.01517   0.00935  -0.2397   0.3724   1.0000
   7.250   1.8405   0.01547   0.00965  -0.2388   0.3608   1.0000
   7.500   1.8625   0.01583   0.00999  -0.2377   0.3458   1.0000
   7.750   1.8826   0.01631   0.01040  -0.2362   0.3257   1.0000
   8.000   1.8995   0.01699   0.01097  -0.2342   0.3022   1.0000
   8.250   1.9137   0.01785   0.01169  -0.2317   0.2767   1.0000
   8.500   1.9273   0.01875   0.01247  -0.2291   0.2532   1.0000
   8.750   1.9395   0.01974   0.01335  -0.2263   0.2324   1.0000
   9.000   1.9521   0.02072   0.01425  -0.2237   0.2153   1.0000
   9.250   1.9646   0.02169   0.01517  -0.2210   0.2000   1.0000
   9.750   1.9877   0.02374   0.01715  -0.2156   0.1728   1.0000
  10.000   1.9978   0.02486   0.01824  -0.2127   0.1605   1.0000
  10.250   2.0076   0.02600   0.01939  -0.2099   0.1509   1.0000
  10.500   2.0141   0.02741   0.02077  -0.2066   0.1421   1.0000
  10.750   2.0241   0.02856   0.02197  -0.2040   0.1350   1.0000
  11.000   2.0280   0.03020   0.02360  -0.2007   0.1282   1.0000
  11.250   2.0385   0.03138   0.02486  -0.1983   0.1237   1.0000
  11.500   2.0437   0.03300   0.02652  -0.1955   0.1189   1.0000
  11.750   2.0451   0.03500   0.02856  -0.1923   0.1145   1.0000
  12.000   2.0543   0.03640   0.03007  -0.1903   0.1113   1.0000
  12.250   2.0588   0.03828   0.03201  -0.1879   0.1073   1.0000
  12.500   2.0585   0.04070   0.03446  -0.1853   0.1035   1.0000
  12.750   2.0617   0.04289   0.03674  -0.1832   0.1003   1.0000
  13.000   2.0675   0.04490   0.03884  -0.1816   0.0967   1.0000
  13.250   2.0676   0.04764   0.04163  -0.1798   0.0929   1.0000
  13.500   2.0638   0.05097   0.04503  -0.1781   0.0899   1.0000
  13.750   2.0674   0.05356   0.04774  -0.1770   0.0875   1.0000
  14.000   2.0698   0.05639   0.05069  -0.1760   0.0852   1.0000
  14.250   2.0689   0.05974   0.05415  -0.1751   0.0834   1.0000
  14.500   2.0662   0.06348   0.05797  -0.1744   0.0812   1.0000
  14.750   2.0591   0.06796   0.06253  -0.1740   0.0786   1.0000
  15.000   2.0577   0.07171   0.06639  -0.1737   0.0760   1.0000
  15.250   2.0576   0.07532   0.07012  -0.1735   0.0739   1.0000
  15.500   2.0543   0.07949   0.07438  -0.1734   0.0710   1.0000
  15.750   2.0477   0.08423   0.07920  -0.1736   0.0686   1.0000
  16.000   2.0395   0.08930   0.08435  -0.1740   0.0658   1.0000
  16.250   2.0388   0.09317   0.08836  -0.1743   0.0637   1.0000
  16.500   2.0342   0.09773   0.09300  -0.1748   0.0600   1.0000
  16.750   2.0254   0.10303   0.09835  -0.1756   0.0567   1.0000
  17.000   2.0213   0.10754   0.10297  -0.1764   0.0530   1.0000
  17.250   2.0122   0.11293   0.10839  -0.1775   0.0478   1.0000
  17.500   2.0001   0.11889   0.11435  -0.1791   0.0401   1.0000
  17.750   1.9904   0.12444   0.11996  -0.1806   0.0354   1.0000
  18.000   1.9713   0.13176   0.12725  -0.1832   0.0271   1.0000
  18.250   1.9588   0.13792   0.13347  -0.1854   0.0227   1.0000
  18.500   1.9428   0.14479   0.14036  -0.1883   0.0174   1.0000
  18.750   1.9223   0.15266   0.14826  -0.1920   0.0117   1.0000
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