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S1221 w/o flap (s1221-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S1221 w/o flap (s1221-il)
Reynolds number: 100,000
Max Cl/Cd: 54.52 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1221-il-100000-n5.txt
Download as CSV file: xf-s1221-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2885   0.10652   0.10177  -0.0262   1.0000   0.0644
  -7.500  -0.2945   0.10365   0.09899  -0.0280   1.0000   0.0648
  -7.250  -0.2965   0.10067   0.09608  -0.0287   1.0000   0.0649
  -6.750  -0.2947   0.08719   0.08263  -0.0285   1.0000   0.0323
  -6.500  -0.2941   0.08497   0.08049  -0.0275   1.0000   0.0319
  -6.250  -0.2976   0.08262   0.07823  -0.0265   1.0000   0.0314
  -6.000  -0.3049   0.08002   0.07574  -0.0255   1.0000   0.0308
  -5.500  -0.3034   0.05888   0.05461  -0.0490   0.9921   0.0270
  -5.250  -0.2443   0.04318   0.03829  -0.0820   0.9814   0.0263
  -5.000  -0.1811   0.03480   0.02904  -0.1001   0.9727   0.0260
  -4.750  -0.1266   0.03020   0.02376  -0.1095   0.9616   0.0261
  -4.500  -0.0784   0.02707   0.02009  -0.1154   0.9466   0.0266
  -4.000   0.0046   0.02341   0.01600  -0.1220   0.8992   0.0298
  -3.750   0.0553   0.02164   0.01396  -0.1263   0.8621   0.0313
  -3.500   0.1343   0.01975   0.01175  -0.1359   0.8075   0.0331
  -3.250   0.2084   0.01867   0.01018  -0.1450   0.7370   0.0364
  -3.000   0.2541   0.01815   0.00923  -0.1488   0.6885   0.0414
  -2.750   0.2938   0.01763   0.00841  -0.1515   0.6505   0.0501
  -2.500   0.3358   0.01674   0.00739  -0.1549   0.6167   0.0832
  -2.250   0.3754   0.01624   0.00732  -0.1581   0.5879   0.2735
  -2.000   0.4057   0.01690   0.00785  -0.1582   0.5646   0.3293
  -1.750   0.4347   0.01728   0.00805  -0.1580   0.5455   0.3529
  -1.500   0.4648   0.01740   0.00792  -0.1582   0.5297   0.3644
  -1.250   0.4945   0.01749   0.00779  -0.1583   0.5160   0.3729
  -1.000   0.5241   0.01755   0.00763  -0.1585   0.5034   0.3800
  -0.750   0.5532   0.01760   0.00755  -0.1585   0.4918   0.3863
  -0.500   0.5829   0.01769   0.00742  -0.1587   0.4817   0.3929
  -0.250   0.6118   0.01776   0.00739  -0.1587   0.4719   0.3986
   0.000   0.6409   0.01787   0.00738  -0.1588   0.4638   0.4055
   0.250   0.6703   0.01798   0.00736  -0.1589   0.4558   0.4125
   0.500   0.6989   0.01812   0.00741  -0.1589   0.4491   0.4188
   0.750   0.7281   0.01824   0.00747  -0.1590   0.4416   0.4271
   1.000   0.7566   0.01839   0.00756  -0.1589   0.4351   0.4353
   1.250   0.7857   0.01856   0.00767  -0.1590   0.4288   0.4456
   1.500   0.8142   0.01871   0.00783  -0.1590   0.4226   0.4551
   1.750   0.8428   0.01892   0.00797  -0.1590   0.4178   0.4661
   2.000   0.8715   0.01913   0.00817  -0.1590   0.4127   0.4794
   2.250   0.8998   0.01932   0.00840  -0.1589   0.4073   0.4942
   2.500   0.9279   0.01953   0.00861  -0.1588   0.4025   0.5116
   2.750   0.9561   0.01977   0.00885  -0.1588   0.3983   0.5316
   3.000   0.9841   0.01998   0.00918  -0.1586   0.3935   0.5551
   3.250   1.0119   0.02020   0.00951  -0.1585   0.3892   0.5840
   3.500   1.0390   0.02042   0.00981  -0.1582   0.3853   0.6219
   3.750   1.0645   0.02063   0.01015  -0.1574   0.3818   0.6747
   4.000   1.0870   0.02077   0.01056  -0.1560   0.3775   0.7511
   4.250   1.1052   0.02086   0.01083  -0.1536   0.3739   0.8396
   4.500   1.1247   0.02096   0.01099  -0.1516   0.3707   1.0000
   4.750   1.1539   0.02140   0.01133  -0.1519   0.3675   1.0000
   5.000   1.1822   0.02186   0.01179  -0.1520   0.3639   1.0000
   5.250   1.2100   0.02231   0.01232  -0.1521   0.3597   1.0000
   5.500   1.2378   0.02278   0.01280  -0.1521   0.3561   1.0000
   5.750   1.2656   0.02325   0.01326  -0.1521   0.3530   1.0000
   6.000   1.2937   0.02373   0.01370  -0.1521   0.3501   1.0000
   6.250   1.3200   0.02427   0.01437  -0.1519   0.3462   1.0000
   6.500   1.3463   0.02480   0.01501  -0.1517   0.3422   1.0000
   6.750   1.3728   0.02531   0.01559  -0.1515   0.3387   1.0000
   7.000   1.3998   0.02579   0.01606  -0.1513   0.3354   1.0000
   7.250   1.4261   0.02633   0.01664  -0.1511   0.3320   1.0000
   7.500   1.4503   0.02695   0.01749  -0.1506   0.3276   1.0000
   7.750   1.4754   0.02747   0.01812  -0.1502   0.3233   1.0000
   8.000   1.5014   0.02793   0.01859  -0.1499   0.3196   1.0000
   8.250   1.5265   0.02847   0.01921  -0.1494   0.3157   1.0000
   8.500   1.5489   0.02912   0.02010  -0.1487   0.3104   1.0000
   8.750   1.5730   0.02959   0.02067  -0.1481   0.3058   1.0000
   9.000   1.5987   0.02997   0.02104  -0.1477   0.3019   1.0000
   9.250   1.6194   0.03073   0.02208  -0.1467   0.2965   1.0000
   9.500   1.6415   0.03129   0.02281  -0.1459   0.2913   1.0000
   9.750   1.6658   0.03163   0.02317  -0.1453   0.2867   1.0000
  10.000   1.6850   0.03236   0.02416  -0.1441   0.2807   1.0000
  10.250   1.7054   0.03286   0.02482  -0.1430   0.2744   1.0000
  10.500   1.7267   0.03321   0.02522  -0.1420   0.2687   1.0000
  10.750   1.7430   0.03395   0.02628  -0.1404   0.2609   1.0000
  11.000   1.7629   0.03422   0.02657  -0.1391   0.2546   1.0000
  11.250   1.7765   0.03512   0.02780  -0.1373   0.2458   1.0000
  11.500   1.7921   0.03565   0.02844  -0.1356   0.2380   1.0000
  11.750   1.8043   0.03650   0.02952  -0.1335   0.2287   1.0000
  12.000   1.8147   0.03745   0.03065  -0.1313   0.2194   1.0000
  12.250   1.8225   0.03838   0.03166  -0.1288   0.2108   1.0000
  12.500   1.8238   0.03977   0.03324  -0.1256   0.2014   1.0000
  12.750   1.8229   0.04135   0.03495  -0.1224   0.1928   1.0000
  13.000   1.8184   0.04329   0.03697  -0.1193   0.1843   1.0000
  13.250   1.8109   0.04586   0.03972  -0.1166   0.1757   1.0000
  13.500   1.7991   0.04903   0.04299  -0.1145   0.1688   1.0000
  13.750   1.7831   0.05323   0.04736  -0.1136   0.1617   1.0000
  14.250   1.7380   0.06542   0.05985  -0.1157   0.1512   1.0000
  14.500   1.7099   0.07339   0.06796  -0.1185   0.1466   1.0000
  14.750   1.6821   0.08162   0.07629  -0.1215   0.1422   1.0000
  15.000   1.6533   0.09045   0.08530  -0.1250   0.1375   1.0000
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