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S1221 w/o flap (s1221-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S1221 w/o flap (s1221-il)
Reynolds number: 50,000
Max Cl/Cd: 36.59 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1221-il-50000-n5.txt
Download as CSV file: xf-s1221-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2794   0.10797   0.10112  -0.0266   1.0000   0.0633
  -7.250  -0.2720   0.10183   0.09515  -0.0268   1.0000   0.0603
  -6.750  -0.2872   0.09408   0.08763  -0.0298   1.0000   0.0545
  -6.500  -0.2876   0.09134   0.08500  -0.0292   1.0000   0.0542
  -6.250  -0.2884   0.08879   0.08257  -0.0284   1.0000   0.0537
  -6.000  -0.2914   0.08598   0.07988  -0.0281   1.0000   0.0532
  -5.750  -0.2920   0.08292   0.07695  -0.0285   1.0000   0.0526
  -5.500  -0.2927   0.07956   0.07371  -0.0295   1.0000   0.0518
  -5.250  -0.2934   0.07563   0.06990  -0.0316   1.0000   0.0511
  -5.000  -0.2924   0.07085   0.06524  -0.0353   1.0000   0.0500
  -4.750  -0.2645   0.05160   0.04533  -0.0679   1.0000   0.0461
  -4.500  -0.2304   0.04566   0.03898  -0.0776   1.0000   0.0459
  -4.250  -0.1756   0.03977   0.03239  -0.0894   0.9963   0.0460
  -4.000  -0.1144   0.03550   0.02761  -0.0992   0.9856   0.0469
  -3.750  -0.0616   0.03263   0.02444  -0.1056   0.9689   0.0487
  -3.500  -0.0117   0.03032   0.02178  -0.1107   0.9474   0.0525
  -3.250   0.0352   0.02832   0.01954  -0.1146   0.9219   0.0565
  -3.000   0.0801   0.02664   0.01775  -0.1177   0.8909   0.0608
  -2.750   0.1312   0.02495   0.01592  -0.1221   0.8564   0.0692
  -2.500   0.1994   0.02290   0.01375  -0.1301   0.8183   0.0931
  -2.250   0.2836   0.02176   0.01319  -0.1415   0.7713   0.3098
  -2.000   0.3244   0.02314   0.01430  -0.1420   0.7268   0.3799
  -1.750   0.3578   0.02352   0.01428  -0.1419   0.6916   0.4044
  -1.500   0.3908   0.02359   0.01393  -0.1425   0.6620   0.4191
  -1.250   0.4244   0.02360   0.01350  -0.1435   0.6373   0.4315
  -1.000   0.4558   0.02362   0.01320  -0.1440   0.6155   0.4419
  -0.750   0.4872   0.02363   0.01292  -0.1446   0.5971   0.4506
  -0.500   0.5196   0.02367   0.01265  -0.1454   0.5808   0.4603
  -0.250   0.5503   0.02374   0.01249  -0.1458   0.5665   0.4686
   0.000   0.5833   0.02384   0.01229  -0.1468   0.5535   0.4782
   0.250   0.6135   0.02395   0.01228  -0.1472   0.5412   0.4869
   0.500   0.6457   0.02411   0.01223  -0.1480   0.5306   0.4979
   0.750   0.6765   0.02427   0.01225  -0.1484   0.5208   0.5085
   1.000   0.7070   0.02445   0.01236  -0.1489   0.5111   0.5196
   1.250   0.7379   0.02465   0.01243  -0.1494   0.5029   0.5333
   1.500   0.7676   0.02489   0.01267  -0.1497   0.4945   0.5484
   1.750   0.7972   0.02514   0.01287  -0.1500   0.4874   0.5650
   2.000   0.8258   0.02541   0.01317  -0.1500   0.4804   0.5836
   2.250   0.8535   0.02569   0.01352  -0.1499   0.4733   0.6060
   2.500   0.8812   0.02596   0.01380  -0.1496   0.4678   0.6335
   2.750   0.9057   0.02629   0.01434  -0.1489   0.4612   0.6664
   3.000   0.9287   0.02656   0.01478  -0.1476   0.4557   0.7118
   3.250   0.9489   0.02674   0.01504  -0.1457   0.4513   0.7783
   3.500   0.9602   0.02678   0.01530  -0.1420   0.4464   0.9027
   3.750   0.9917   0.02740   0.01588  -0.1431   0.4403   1.0000
   4.000   1.0230   0.02806   0.01638  -0.1440   0.4355   1.0000
   4.250   1.0522   0.02882   0.01708  -0.1445   0.4307   1.0000
   4.500   1.0794   0.02966   0.01800  -0.1448   0.4252   1.0000
   4.750   1.1075   0.03039   0.01869  -0.1450   0.4204   1.0000
   5.000   1.1368   0.03107   0.01925  -0.1453   0.4165   1.0000
   5.250   1.1607   0.03213   0.02047  -0.1451   0.4112   1.0000
   5.500   1.1861   0.03307   0.02152  -0.1451   0.4064   1.0000
   5.750   1.2130   0.03386   0.02230  -0.1450   0.4023   1.0000
   6.000   1.2398   0.03470   0.02313  -0.1450   0.3985   1.0000
   6.250   1.2604   0.03604   0.02474  -0.1445   0.3931   1.0000
   6.500   1.2839   0.03712   0.02593  -0.1442   0.3887   1.0000
   6.750   1.3101   0.03795   0.02678  -0.1440   0.3848   1.0000
   7.000   1.3327   0.03912   0.02806  -0.1436   0.3806   1.0000
   7.250   1.3499   0.04073   0.02997  -0.1427   0.3751   1.0000
   7.500   1.3723   0.04186   0.03122  -0.1422   0.3706   1.0000
   7.750   1.3990   0.04258   0.03194  -0.1420   0.3670   1.0000
   8.000   1.4109   0.04464   0.03435  -0.1408   0.3611   1.0000
   8.250   1.4273   0.04625   0.03617  -0.1398   0.3558   1.0000
   8.500   1.4524   0.04698   0.03696  -0.1394   0.3516   1.0000
   8.750   1.4650   0.04891   0.03912  -0.1381   0.3463   1.0000
   9.000   1.4723   0.05124   0.04176  -0.1366   0.3402   1.0000
   9.250   1.4969   0.05185   0.04244  -0.1360   0.3356   1.0000
   9.500   1.5035   0.05418   0.04501  -0.1344   0.3300   1.0000
   9.750   1.5007   0.05722   0.04834  -0.1323   0.3234   1.0000
  10.000   1.5304   0.05716   0.04835  -0.1318   0.3189   1.0000
  10.250   1.5024   0.06242   0.05396  -0.1286   0.3122   1.0000
  10.500   1.4846   0.06640   0.05813  -0.1260   0.3061   1.0000
  10.750   1.5449   0.06346   0.05522  -0.1265   0.3019   1.0000
  11.000   1.3546   0.08847   0.08045  -0.1282   0.2886   1.0000
  11.250   1.3987   0.08495   0.07707  -0.1249   0.2865   1.0000
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