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S1221 w/o flap (s1221-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S1221 w/o flap (s1221-il)
Reynolds number: 200,000
Max Cl/Cd: 76.51 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1221-il-200000-n5.txt
Download as CSV file: xf-s1221-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3050   0.09052   0.08712  -0.0264   1.0000   0.0188
  -7.250  -0.3024   0.08826   0.08491  -0.0261   1.0000   0.0186
  -7.000  -0.3061   0.08482   0.08154  -0.0263   1.0000   0.0186
  -6.750  -0.3034   0.08112   0.07788  -0.0283   0.9987   0.0186
  -6.500  -0.3021   0.07194   0.06872  -0.0375   0.9914   0.0188
  -6.250  -0.2867   0.06688   0.06368  -0.0436   0.9828   0.0186
  -6.000  -0.2785   0.05805   0.05486  -0.0535   0.9697   0.0183
  -5.250  -0.1281   0.02428   0.01884  -0.1193   0.9281   0.0169
  -5.000  -0.0810   0.02168   0.01581  -0.1245   0.9058   0.0170
  -4.750  -0.0087   0.01911   0.01275  -0.1342   0.8602   0.0174
  -4.500   0.1136   0.01683   0.00959  -0.1539   0.7519   0.0184
  -4.250   0.1504   0.01635   0.00867  -0.1558   0.6937   0.0189
  -4.000   0.1814   0.01587   0.00798  -0.1567   0.6530   0.0197
  -3.750   0.2112   0.01558   0.00747  -0.1573   0.6147   0.0212
  -3.500   0.2411   0.01532   0.00694  -0.1577   0.5824   0.0227
  -3.250   0.2727   0.01495   0.00638  -0.1587   0.5558   0.0240
  -3.000   0.3041   0.01468   0.00590  -0.1595   0.5345   0.0257
  -2.750   0.3358   0.01443   0.00545  -0.1603   0.5164   0.0283
  -2.500   0.3676   0.01420   0.00505  -0.1611   0.5007   0.0338
  -2.250   0.4018   0.01373   0.00461  -0.1627   0.4862   0.0734
  -2.000   0.4375   0.01311   0.00446  -0.1650   0.4729   0.2329
  -1.750   0.4665   0.01329   0.00461  -0.1650   0.4618   0.2854
  -1.500   0.4949   0.01356   0.00479  -0.1649   0.4517   0.3163
  -1.250   0.5238   0.01367   0.00479  -0.1648   0.4429   0.3285
  -1.000   0.5525   0.01376   0.00477  -0.1647   0.4348   0.3351
  -0.750   0.5815   0.01382   0.00471  -0.1647   0.4273   0.3410
  -0.500   0.6103   0.01388   0.00468  -0.1647   0.4199   0.3456
  -0.250   0.6391   0.01395   0.00468  -0.1647   0.4132   0.3498
   0.000   0.6680   0.01402   0.00468  -0.1646   0.4062   0.3550
   0.250   0.6965   0.01415   0.00468  -0.1646   0.4003   0.3607
   0.500   0.7255   0.01420   0.00475  -0.1646   0.3948   0.3658
   0.750   0.7543   0.01430   0.00480  -0.1646   0.3894   0.3716
   1.000   0.7828   0.01444   0.00486  -0.1645   0.3847   0.3779
   1.250   0.8115   0.01454   0.00497  -0.1645   0.3802   0.3843
   1.500   0.8401   0.01465   0.00507  -0.1644   0.3751   0.3925
   1.750   0.8686   0.01478   0.00519  -0.1644   0.3705   0.4010
   2.000   0.8968   0.01496   0.00532  -0.1643   0.3666   0.4113
   2.250   0.9255   0.01508   0.00549  -0.1643   0.3629   0.4216
   2.500   0.9542   0.01521   0.00567  -0.1643   0.3589   0.4334
   2.750   0.9826   0.01537   0.00584  -0.1643   0.3549   0.4471
   3.250   1.0393   0.01574   0.00625  -0.1642   0.3481   0.4808
   3.500   1.0680   0.01588   0.00650  -0.1642   0.3448   0.5026
   3.750   1.0965   0.01604   0.00675  -0.1643   0.3415   0.5284
   4.000   1.1249   0.01621   0.00702  -0.1643   0.3382   0.5583
   4.250   1.1530   0.01640   0.00727  -0.1642   0.3352   0.5945
   4.500   1.1807   0.01658   0.00758  -0.1640   0.3322   0.6426
   4.750   1.2066   0.01668   0.00792  -0.1634   0.3294   0.7181
   5.000   1.2303   0.01680   0.00822  -0.1622   0.3266   0.7951
   5.250   1.2491   0.01683   0.00840  -0.1600   0.3239   0.8719
   5.500   1.2699   0.01693   0.00855  -0.1583   0.3212   1.0000
   5.750   1.2976   0.01727   0.00884  -0.1582   0.3184   1.0000
   6.000   1.3253   0.01760   0.00919  -0.1582   0.3157   1.0000
   6.250   1.3528   0.01789   0.00955  -0.1581   0.3126   1.0000
   6.500   1.3800   0.01819   0.00991  -0.1579   0.3091   1.0000
   6.750   1.4070   0.01849   0.01023  -0.1577   0.3058   1.0000
   7.000   1.4337   0.01884   0.01056  -0.1574   0.3027   1.0000
   7.250   1.4602   0.01918   0.01096  -0.1572   0.2993   1.0000
   7.500   1.4866   0.01947   0.01136  -0.1569   0.2951   1.0000
   7.750   1.5126   0.01977   0.01172  -0.1565   0.2910   1.0000
   8.000   1.5383   0.02011   0.01207  -0.1561   0.2873   1.0000
   8.250   1.5640   0.02049   0.01250  -0.1557   0.2837   1.0000
   8.500   1.5894   0.02081   0.01297  -0.1553   0.2793   1.0000
   8.750   1.6145   0.02113   0.01338  -0.1548   0.2748   1.0000
   9.000   1.6389   0.02150   0.01375  -0.1542   0.2706   1.0000
   9.250   1.6635   0.02183   0.01424  -0.1537   0.2649   1.0000
   9.500   1.6875   0.02214   0.01465  -0.1530   0.2587   1.0000
   9.750   1.7108   0.02250   0.01507  -0.1523   0.2528   1.0000
  10.000   1.7343   0.02283   0.01553  -0.1515   0.2447   1.0000
  10.250   1.7567   0.02321   0.01599  -0.1507   0.2368   1.0000
  10.500   1.7787   0.02363   0.01649  -0.1498   0.2277   1.0000
  10.750   1.8004   0.02411   0.01707  -0.1488   0.2182   1.0000
  11.000   1.8205   0.02468   0.01768  -0.1477   0.2082   1.0000
  11.250   1.8391   0.02536   0.01840  -0.1464   0.1971   1.0000
  11.500   1.8565   0.02614   0.01923  -0.1450   0.1846   1.0000
  11.750   1.8719   0.02706   0.02018  -0.1433   0.1716   1.0000
  12.000   1.8842   0.02817   0.02131  -0.1412   0.1582   1.0000
  12.250   1.8933   0.02947   0.02263  -0.1387   0.1455   1.0000
  12.500   1.8977   0.03086   0.02406  -0.1356   0.1348   1.0000
  12.750   1.8991   0.03243   0.02568  -0.1321   0.1257   1.0000
  13.000   1.8976   0.03428   0.02758  -0.1287   0.1175   1.0000
  13.250   1.8967   0.03619   0.02959  -0.1256   0.1101   1.0000
  13.500   1.8901   0.03869   0.03217  -0.1226   0.1040   1.0000
  13.750   1.8848   0.04133   0.03494  -0.1203   0.0981   1.0000
  14.000   1.8729   0.04491   0.03863  -0.1186   0.0933   1.0000
  14.250   1.8619   0.04893   0.04280  -0.1180   0.0893   1.0000
  14.500   1.8480   0.05392   0.04795  -0.1185   0.0856   1.0000
  14.750   1.8293   0.06014   0.05432  -0.1200   0.0826   1.0000
  15.000   1.8094   0.06697   0.06132  -0.1222   0.0802   1.0000
  15.250   1.7910   0.07382   0.06835  -0.1244   0.0776   1.0000
  15.500   1.7700   0.08118   0.07587  -0.1269   0.0753   1.0000
  15.750   1.7479   0.08884   0.08367  -0.1296   0.0732   1.0000
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