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S1221 w/o flap (s1221-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S1221 w/o flap (s1221-il)
Reynolds number: 100,000
Max Cl/Cd: 45.22 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1221-il-100000.txt
Download as CSV file: xf-s1221-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -6.750  -0.2569   0.09921   0.09475  -0.0210   1.0000   0.1121
  -6.500  -0.2707   0.09805   0.09372  -0.0220   1.0000   0.1171
  -6.250  -0.3068   0.09855   0.09443  -0.0236   1.0000   0.1185
  -6.000  -0.2695   0.09254   0.08838  -0.0201   1.0000   0.1217
  -5.750  -0.2613   0.09027   0.08618  -0.0183   1.0000   0.1254
  -5.500  -0.2694   0.08883   0.08486  -0.0168   1.0000   0.1296
  -5.250  -0.3016   0.08724   0.08351  -0.0238   1.0000   0.1342
  -5.000  -0.2870   0.08445   0.08076  -0.0166   1.0000   0.1365
  -4.750  -0.2812   0.08257   0.07895  -0.0138   1.0000   0.1401
  -4.500  -0.2954   0.08109   0.07766  -0.0184   1.0000   0.1480
  -4.250  -0.2653   0.07684   0.07344  -0.0208   0.9938   0.1530
  -4.000  -0.1367   0.03886   0.03395  -0.0951   0.9883   0.0753
  -3.750  -0.0503   0.03048   0.02436  -0.1114   0.9849   0.0634
  -3.500   0.0205   0.02682   0.02003  -0.1208   0.9729   0.0640
  -3.250   0.0852   0.02394   0.01670  -0.1278   0.9561   0.0645
  -3.000   0.1412   0.02136   0.01397  -0.1325   0.9304   0.0658
  -2.750   0.1962   0.01922   0.01197  -0.1367   0.8939   0.0702
  -2.500   0.2822   0.01709   0.00972  -0.1469   0.8400   0.0886
  -2.250   0.3788   0.01701   0.00995  -0.1596   0.7536   0.3635
  -2.000   0.4088   0.01854   0.01128  -0.1582   0.7041   0.4081
  -1.750   0.4374   0.01916   0.01161  -0.1574   0.6705   0.4316
  -1.500   0.4676   0.01936   0.01150  -0.1576   0.6433   0.4466
  -1.250   0.4958   0.01949   0.01139  -0.1572   0.6223   0.4569
  -1.000   0.5269   0.01952   0.01112  -0.1578   0.6037   0.4665
  -0.750   0.5573   0.01958   0.01093  -0.1582   0.5874   0.4756
  -0.500   0.5880   0.01959   0.01075  -0.1587   0.5727   0.4833
  -0.250   0.6183   0.01968   0.01068  -0.1592   0.5599   0.4915
   0.000   0.6495   0.01978   0.01058  -0.1599   0.5490   0.4991
   0.250   0.6793   0.01991   0.01056  -0.1602   0.5385   0.5068
   0.500   0.7096   0.02005   0.01061  -0.1607   0.5285   0.5158
   0.750   0.7396   0.02025   0.01065  -0.1610   0.5201   0.5252
   1.000   0.7692   0.02043   0.01083  -0.1613   0.5119   0.5344
   1.250   0.7998   0.02067   0.01095  -0.1618   0.5047   0.5466
   1.500   0.8283   0.02093   0.01122  -0.1619   0.4979   0.5590
   1.750   0.8570   0.02115   0.01148  -0.1620   0.4906   0.5735
   2.000   0.8869   0.02146   0.01169  -0.1622   0.4850   0.5904
   2.250   0.9150   0.02176   0.01214  -0.1623   0.4788   0.6105
   2.500   0.9425   0.02204   0.01252  -0.1621   0.4732   0.6346
   2.750   0.9698   0.02237   0.01286  -0.1618   0.4684   0.6663
   3.000   0.9939   0.02271   0.01344  -0.1608   0.4631   0.7061
   3.250   1.0160   0.02298   0.01394  -0.1594   0.4579   0.7650
   3.500   1.0276   0.02296   0.01415  -0.1554   0.4542   0.8615
   3.750   1.0528   0.02328   0.01433  -0.1549   0.4506   1.0000
   4.000   1.0823   0.02402   0.01514  -0.1557   0.4453   1.0000
   4.250   1.1113   0.02469   0.01581  -0.1561   0.4401   1.0000
   4.500   1.1408   0.02534   0.01636  -0.1565   0.4359   1.0000
   4.750   1.1693   0.02618   0.01715  -0.1567   0.4324   1.0000
   5.000   1.1943   0.02709   0.01825  -0.1566   0.4275   1.0000
   5.250   1.2210   0.02786   0.01907  -0.1565   0.4228   1.0000
   5.500   1.2491   0.02854   0.01970  -0.1566   0.4188   1.0000
   5.750   1.2759   0.02951   0.02067  -0.1566   0.4153   1.0000
   6.000   1.2979   0.03066   0.02210  -0.1560   0.4101   1.0000
   6.250   1.3234   0.03150   0.02301  -0.1558   0.4054   1.0000
   6.500   1.3512   0.03217   0.02364  -0.1557   0.4015   1.0000
   6.750   1.3744   0.03337   0.02498  -0.1553   0.3972   1.0000
   7.000   1.3944   0.03470   0.02655  -0.1545   0.3915   1.0000
   7.250   1.4205   0.03542   0.02730  -0.1542   0.3870   1.0000
   7.500   1.4498   0.03597   0.02777  -0.1543   0.3832   1.0000
   7.750   1.4632   0.03790   0.03010  -0.1529   0.3768   1.0000
   8.000   1.4866   0.03875   0.03104  -0.1523   0.3714   1.0000
   8.250   1.5175   0.03890   0.03110  -0.1524   0.3672   1.0000
   8.500   1.5288   0.04105   0.03362  -0.1508   0.3607   1.0000
   8.750   1.5512   0.04184   0.03453  -0.1500   0.3548   1.0000
   9.000   1.5843   0.04167   0.03422  -0.1502   0.3506   1.0000
   9.250   1.5899   0.04421   0.03721  -0.1481   0.3431   1.0000
   9.500   1.6165   0.04439   0.03743  -0.1476   0.3374   1.0000
   9.750   1.6484   0.04416   0.03710  -0.1476   0.3324   1.0000
  10.000   1.6519   0.04647   0.03985  -0.1451   0.3241   1.0000
  10.250   1.6920   0.04494   0.03813  -0.1456   0.3186   1.0000
  10.500   1.6950   0.04720   0.04077  -0.1430   0.3103   1.0000
  10.750   1.7324   0.04561   0.03906  -0.1431   0.3036   1.0000
  11.000   1.7422   0.04693   0.04065  -0.1410   0.2955   1.0000
  11.250   1.7766   0.04540   0.03902  -0.1408   0.2879   1.0000
  11.500   1.7867   0.04634   0.04020  -0.1385   0.2794   1.0000
  11.750   1.8240   0.04433   0.03801  -0.1386   0.2712   1.0000
  12.000   1.8256   0.04574   0.03978  -0.1354   0.2619   1.0000
  12.250   1.8556   0.04436   0.03827  -0.1347   0.2532   1.0000
  12.500   1.8608   0.04501   0.03917  -0.1317   0.2435   1.0000
  12.750   1.8670   0.04559   0.03992  -0.1287   0.2341   1.0000
  13.000   1.8827   0.04516   0.03942  -0.1266   0.2243   1.0000
  13.250   1.8711   0.04679   0.04129  -0.1218   0.2156   1.0000
  13.500   1.8655   0.04819   0.04277  -0.1180   0.2070   1.0000
  13.750   1.8673   0.04910   0.04357  -0.1152   0.1972   1.0000
  14.000   1.8443   0.05283   0.04760  -0.1119   0.1896   1.0000
  14.250   1.8361   0.05554   0.05029  -0.1101   0.1810   1.0000
  14.500   1.8182   0.05981   0.05469  -0.1092   0.1734   1.0000
  14.750   1.8031   0.06437   0.05931  -0.1090   0.1661   1.0000
  15.000   1.7902   0.06896   0.06391  -0.1095   0.1586   1.0000
  15.250   1.7713   0.07492   0.06999  -0.1107   0.1522   1.0000
  15.500   1.7652   0.07902   0.07403  -0.1113   0.1446   1.0000
  15.750   1.7443   0.08585   0.08103  -0.1134   0.1393   1.0000
  16.000   1.7329   0.09126   0.08651  -0.1150   0.1334   1.0000
  16.250   1.7288   0.09555   0.09080  -0.1157   0.1276   1.0000
  16.500   1.7044   0.10366   0.09916  -0.1193   0.1240   1.0000
  16.750   1.4164   0.17504   0.17121  -0.1646   0.1307   1.0000
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