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S1221 w/o flap (s1221-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S1221 w/o flap (s1221-il)
Reynolds number: 500,000
Max Cl/Cd: 107.54 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1221-il-500000.txt
Download as CSV file: xf-s1221-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1221  w/o flap                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3065   0.09567   0.09353  -0.0233   1.0000   0.0227
  -7.500  -0.3132   0.09092   0.08883  -0.0252   1.0000   0.0228
  -7.250  -0.3126   0.08830   0.08624  -0.0242   1.0000   0.0230
  -7.000  -0.3088   0.08667   0.08465  -0.0229   1.0000   0.0232
  -6.750  -0.2952   0.08390   0.08189  -0.0252   0.9987   0.0235
  -6.500  -0.2698   0.08057   0.07857  -0.0305   0.9955   0.0244
  -6.250  -0.2521   0.07611   0.07412  -0.0363   0.9913   0.0251
  -6.000  -0.2389   0.04472   0.04241  -0.0894   0.9776   0.0277
  -5.750  -0.2152   0.04331   0.04112  -0.0889   0.9708   0.0281
  -5.500  -0.1755   0.03840   0.03607  -0.0996   0.9627   0.0290
  -5.250  -0.1085   0.02902   0.02582  -0.1215   0.9546   0.0335
  -4.500   0.1152   0.01361   0.00838  -0.1557   0.8730   0.0195
  -4.250   0.1854   0.01306   0.00693  -0.1645   0.7217   0.0193
  -4.000   0.2129   0.01266   0.00624  -0.1644   0.6717   0.0194
  -3.750   0.2420   0.01227   0.00564  -0.1647   0.6269   0.0198
  -3.500   0.2715   0.01200   0.00515  -0.1651   0.5858   0.0204
  -3.250   0.3019   0.01177   0.00471  -0.1656   0.5530   0.0213
  -3.000   0.3330   0.01156   0.00432  -0.1662   0.5279   0.0223
  -2.750   0.3651   0.01128   0.00389  -0.1671   0.5076   0.0236
  -2.500   0.3962   0.01113   0.00361  -0.1677   0.4909   0.0259
  -2.250   0.4275   0.01097   0.00334  -0.1683   0.4767   0.0306
  -2.000   0.4683   0.00994   0.00290  -0.1718   0.4635   0.2315
  -1.750   0.4972   0.01004   0.00295  -0.1718   0.4521   0.2672
  -1.500   0.5260   0.01013   0.00299  -0.1717   0.4419   0.2843
  -1.250   0.5542   0.01030   0.00308  -0.1715   0.4324   0.3022
  -1.000   0.5827   0.01045   0.00320  -0.1713   0.4240   0.3206
  -0.750   0.6110   0.01061   0.00327  -0.1712   0.4162   0.3319
  -0.500   0.6400   0.01066   0.00329  -0.1711   0.4092   0.3385
  -0.250   0.6686   0.01078   0.00330  -0.1710   0.4024   0.3428
   0.000   0.6977   0.01080   0.00330  -0.1711   0.3962   0.3474
   0.250   0.7267   0.01085   0.00333  -0.1710   0.3900   0.3518
   0.500   0.7551   0.01097   0.00337  -0.1709   0.3842   0.3566
   0.750   0.7841   0.01104   0.00341  -0.1709   0.3793   0.3618
   1.000   0.8132   0.01108   0.00348  -0.1709   0.3745   0.3680
   1.250   0.8417   0.01120   0.00354  -0.1709   0.3699   0.3745
   1.500   0.8703   0.01134   0.00365  -0.1708   0.3653   0.3814
   1.750   0.8993   0.01138   0.00373  -0.1709   0.3614   0.3899
   2.000   0.9282   0.01146   0.00383  -0.1709   0.3575   0.3991
   2.250   0.9568   0.01159   0.00394  -0.1708   0.3539   0.4103
   2.500   0.9852   0.01178   0.00412  -0.1708   0.3500   0.4230
   2.750   1.0142   0.01185   0.00426  -0.1708   0.3471   0.4385
   3.000   1.0431   0.01192   0.00440  -0.1709   0.3438   0.4570
   3.250   1.0719   0.01202   0.00454  -0.1709   0.3405   0.4784
   3.500   1.1007   0.01215   0.00472  -0.1710   0.3375   0.5035
   3.750   1.1292   0.01236   0.00496  -0.1710   0.3343   0.5336
   4.000   1.1583   0.01247   0.00519  -0.1712   0.3318   0.5707
   4.250   1.1877   0.01252   0.00540  -0.1713   0.3292   0.6201
   4.500   1.2167   0.01254   0.00566  -0.1714   0.3262   0.7044
   4.750   1.2436   0.01260   0.00590  -0.1710   0.3235   0.7906
   5.000   1.2677   0.01268   0.00611  -0.1699   0.3209   0.8572
   5.250   1.2836   0.01273   0.00623  -0.1671   0.3181   1.0000
   5.500   1.3118   0.01293   0.00645  -0.1670   0.3155   1.0000
   5.750   1.3399   0.01308   0.00664  -0.1670   0.3127   1.0000
   6.000   1.3677   0.01326   0.00683  -0.1668   0.3096   1.0000
   6.250   1.3952   0.01345   0.00702  -0.1667   0.3063   1.0000
   6.500   1.4223   0.01377   0.00728  -0.1665   0.3026   1.0000
   6.750   1.4496   0.01399   0.00754  -0.1663   0.2995   1.0000
   7.000   1.4770   0.01415   0.00776  -0.1661   0.2965   1.0000
   7.250   1.5041   0.01434   0.00798  -0.1659   0.2933   1.0000
   7.500   1.5309   0.01455   0.00821  -0.1656   0.2900   1.0000
   7.750   1.5571   0.01494   0.00855  -0.1653   0.2860   1.0000
   8.000   1.5839   0.01508   0.00878  -0.1650   0.2827   1.0000
   8.250   1.6105   0.01521   0.00898  -0.1647   0.2785   1.0000
   8.500   1.6367   0.01539   0.00918  -0.1644   0.2740   1.0000
   8.750   1.6622   0.01568   0.00947  -0.1639   0.2689   1.0000
   9.000   1.6888   0.01575   0.00964  -0.1636   0.2634   1.0000
   9.250   1.7145   0.01596   0.00987  -0.1632   0.2582   1.0000
   9.500   1.7398   0.01624   0.01018  -0.1627   0.2531   1.0000
   9.750   1.7658   0.01642   0.01045  -0.1624   0.2476   1.0000
  10.000   1.7905   0.01671   0.01074  -0.1618   0.2414   1.0000
  10.250   1.8159   0.01694   0.01106  -0.1614   0.2345   1.0000
  10.500   1.8398   0.01730   0.01140  -0.1607   0.2261   1.0000
  10.750   1.8644   0.01761   0.01178  -0.1602   0.2170   1.0000
  11.000   1.8875   0.01805   0.01223  -0.1595   0.2063   1.0000
  11.250   1.9093   0.01862   0.01277  -0.1586   0.1930   1.0000
  11.500   1.9299   0.01931   0.01343  -0.1575   0.1777   1.0000
  11.750   1.9486   0.02018   0.01424  -0.1562   0.1611   1.0000
  12.000   1.9652   0.02121   0.01520  -0.1547   0.1451   1.0000
  12.250   1.9802   0.02236   0.01629  -0.1529   0.1303   1.0000
  12.500   1.9938   0.02355   0.01745  -0.1509   0.1166   1.0000
  12.750   2.0052   0.02484   0.01871  -0.1487   0.1039   1.0000
  13.000   2.0142   0.02620   0.02005  -0.1460   0.0931   1.0000
  13.250   2.0187   0.02755   0.02143  -0.1426   0.0841   1.0000
  13.500   2.0204   0.02902   0.02294  -0.1389   0.0769   1.0000
  14.000   2.0183   0.03257   0.02659  -0.1318   0.0657   1.0000
  14.250   2.0117   0.03494   0.02901  -0.1283   0.0615   1.0000
  14.500   2.0073   0.03733   0.03151  -0.1256   0.0585   1.0000
  14.750   2.0001   0.04024   0.03453  -0.1234   0.0559   1.0000
  15.000   1.9871   0.04418   0.03859  -0.1221   0.0538   1.0000
  15.250   1.9692   0.04950   0.04406  -0.1223   0.0522   1.0000
  15.500   1.9516   0.05561   0.05033  -0.1236   0.0509   1.0000
  15.750   1.9348   0.06205   0.05696  -0.1255   0.0500   1.0000
  16.000   1.9140   0.06942   0.06451  -0.1279   0.0491   1.0000
  16.250   1.8894   0.07750   0.07277  -0.1306   0.0485   1.0000
  16.500   1.8633   0.08589   0.08132  -0.1333   0.0480   1.0000
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