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S1221 w/o flap (s1221-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S1221 w/o flap (s1221-il)
Reynolds number: 500,000
Max Cl/Cd: 109.97 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1221-il-500000-n5.txt
Download as CSV file: xf-s1221-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2647   0.08401   0.08172  -0.0408   0.9886   0.0102
  -7.500  -0.3482   0.05994   0.05762  -0.0529   0.9803   0.0097
  -7.250  -0.3733   0.04314   0.04058  -0.0739   0.9627   0.0095
  -6.750  -0.2691   0.02333   0.01939  -0.1199   0.9391   0.0096
  -6.500  -0.2203   0.02024   0.01591  -0.1273   0.9245   0.0099
  -6.250  -0.0596   0.01688   0.01171  -0.1577   0.8101   0.0105
  -6.000  -0.0324   0.01645   0.01064  -0.1581   0.7090   0.0106
  -5.750  -0.0048   0.01579   0.00966  -0.1586   0.6671   0.0107
  -5.500   0.0238   0.01519   0.00880  -0.1591   0.6277   0.0108
  -5.250   0.0528   0.01467   0.00801  -0.1596   0.5899   0.0110
  -5.000   0.0827   0.01418   0.00731  -0.1603   0.5591   0.0112
  -4.750   0.1133   0.01375   0.00668  -0.1611   0.5340   0.0114
  -4.500   0.1444   0.01334   0.00611  -0.1619   0.5133   0.0116
  -4.250   0.1757   0.01298   0.00560  -0.1627   0.4959   0.0120
  -4.000   0.2070   0.01268   0.00516  -0.1635   0.4809   0.0123
  -3.750   0.2389   0.01235   0.00470  -0.1644   0.4668   0.0127
  -3.500   0.2706   0.01207   0.00431  -0.1652   0.4540   0.0132
  -3.250   0.3017   0.01187   0.00402  -0.1658   0.4431   0.0138
  -2.500   0.3938   0.01144   0.00332  -0.1672   0.4163   0.0174
  -2.250   0.4245   0.01131   0.00313  -0.1676   0.4089   0.0199
  -2.000   0.4555   0.01118   0.00296  -0.1681   0.4014   0.0301
  -1.750   0.4885   0.01085   0.00277  -0.1693   0.3947   0.0860
  -1.500   0.5230   0.01039   0.00264  -0.1710   0.3872   0.2082
  -1.250   0.5526   0.01040   0.00270  -0.1712   0.3808   0.2554
  -1.000   0.5818   0.01044   0.00277  -0.1713   0.3749   0.2825
  -0.750   0.6106   0.01052   0.00281  -0.1712   0.3693   0.2967
  -0.500   0.6395   0.01059   0.00283  -0.1712   0.3645   0.3033
  -0.250   0.6684   0.01064   0.00283  -0.1711   0.3599   0.3068
   0.000   0.6973   0.01070   0.00284  -0.1711   0.3550   0.3099
   0.250   0.7261   0.01078   0.00287  -0.1711   0.3503   0.3135
   0.500   0.7551   0.01084   0.00291  -0.1710   0.3461   0.3181
   0.750   0.7839   0.01091   0.00295  -0.1710   0.3417   0.3227
   1.000   0.8125   0.01100   0.00301  -0.1709   0.3378   0.3268
   1.250   0.8411   0.01109   0.00308  -0.1708   0.3341   0.3317
   1.500   0.8699   0.01117   0.00316  -0.1708   0.3309   0.3373
   1.750   0.8985   0.01125   0.00323  -0.1707   0.3273   0.3429
   2.000   0.9272   0.01134   0.00332  -0.1707   0.3237   0.3494
   2.250   0.9556   0.01145   0.00343  -0.1706   0.3206   0.3569
   2.500   0.9839   0.01158   0.00355  -0.1705   0.3177   0.3650
   2.750   1.0124   0.01167   0.00367  -0.1705   0.3153   0.3750
   3.000   1.0410   0.01176   0.00380  -0.1704   0.3125   0.3854
   3.250   1.0694   0.01186   0.00393  -0.1704   0.3095   0.3965
   3.500   1.0977   0.01198   0.00408  -0.1703   0.3067   0.4092
   3.750   1.1258   0.01212   0.00424  -0.1702   0.3042   0.4231
   4.000   1.1539   0.01228   0.00442  -0.1701   0.3017   0.4384
   4.250   1.1822   0.01239   0.00460  -0.1701   0.2998   0.4557
   4.500   1.2106   0.01249   0.00477  -0.1700   0.2975   0.4752
   4.750   1.2390   0.01261   0.00497  -0.1700   0.2948   0.4980
   5.000   1.2673   0.01273   0.00517  -0.1700   0.2923   0.5259
   5.250   1.2955   0.01287   0.00539  -0.1700   0.2898   0.5579
   5.500   1.3236   0.01303   0.00563  -0.1700   0.2870   0.5959
   5.750   1.3521   0.01314   0.00589  -0.1700   0.2844   0.6479
   6.000   1.3804   0.01318   0.00617  -0.1700   0.2816   0.7326
   6.250   1.4073   0.01328   0.00641  -0.1696   0.2782   0.7907
   6.500   1.4327   0.01339   0.00662  -0.1690   0.2745   0.8382
   6.750   1.4521   0.01344   0.00678  -0.1670   0.2712   0.9137
   7.000   1.4758   0.01357   0.00696  -0.1660   0.2684   1.0000
   7.250   1.5031   0.01375   0.00719  -0.1658   0.2653   1.0000
   7.500   1.5301   0.01395   0.00743  -0.1656   0.2618   1.0000
   7.750   1.5567   0.01419   0.00768  -0.1653   0.2577   1.0000
   8.000   1.5831   0.01445   0.00794  -0.1650   0.2536   1.0000
   8.250   1.6099   0.01464   0.00818  -0.1647   0.2483   1.0000
   8.500   1.6359   0.01491   0.00845  -0.1643   0.2421   1.0000
   8.750   1.6619   0.01516   0.00873  -0.1640   0.2347   1.0000
   9.000   1.6871   0.01550   0.00903  -0.1635   0.2251   1.0000
   9.250   1.7125   0.01581   0.00937  -0.1631   0.2159   1.0000
   9.500   1.7372   0.01620   0.00975  -0.1626   0.2066   1.0000
   9.750   1.7612   0.01666   0.01018  -0.1620   0.1966   1.0000
  10.000   1.7847   0.01716   0.01067  -0.1613   0.1848   1.0000
  10.250   1.8069   0.01779   0.01124  -0.1605   0.1704   1.0000
  10.500   1.8281   0.01853   0.01192  -0.1595   0.1549   1.0000
  10.750   1.8486   0.01931   0.01266  -0.1585   0.1411   1.0000
  11.000   1.8684   0.02014   0.01346  -0.1573   0.1284   1.0000
  11.250   1.8871   0.02104   0.01432  -0.1561   0.1161   1.0000
  11.500   1.9051   0.02197   0.01522  -0.1547   0.1051   1.0000
  11.750   1.9227   0.02287   0.01613  -0.1532   0.0954   1.0000
  12.000   1.9394   0.02380   0.01707  -0.1517   0.0872   1.0000
  12.250   1.9540   0.02485   0.01813  -0.1498   0.0793   1.0000
  12.500   1.9669   0.02596   0.01925  -0.1478   0.0718   1.0000
  12.750   1.9774   0.02711   0.02043  -0.1453   0.0654   1.0000
  13.250   1.9868   0.02967   0.02308  -0.1387   0.0557   1.0000
  13.500   1.9884   0.03123   0.02470  -0.1353   0.0520   1.0000
  13.750   1.9911   0.03278   0.02634  -0.1323   0.0491   1.0000
  14.000   1.9906   0.03466   0.02830  -0.1294   0.0463   1.0000
  14.250   1.9859   0.03703   0.03075  -0.1265   0.0439   1.0000
  14.500   1.9821   0.03956   0.03341  -0.1244   0.0422   1.0000
  14.750   1.9759   0.04264   0.03661  -0.1229   0.0406   1.0000
  15.000   1.9651   0.04673   0.04083  -0.1224   0.0389   1.0000
  15.250   1.9521   0.05179   0.04604  -0.1231   0.0380   1.0000
  15.500   1.9342   0.05816   0.05258  -0.1248   0.0369   1.0000
  16.000   1.8924   0.07292   0.06770  -0.1296   0.0358   1.0000
  16.250   1.8688   0.08090   0.07585  -0.1322   0.0356   1.0000
  16.500   1.8451   0.08895   0.08407  -0.1350   0.0353   1.0000
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