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S1221 w/ 4 deg flap (s1221-flap-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S1221 w/ 4 deg flap (s1221-flap-il)
Reynolds number: 200,000
Max Cl/Cd: 76.29 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1221-flap-il-200000-n5.txt
Download as CSV file: xf-s1221-flap-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1221  w/ 4 deg 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2236   0.09565   0.09216  -0.0428   0.9839   0.0224
  -8.000  -0.2113   0.09183   0.08835  -0.0459   0.9799   0.0221
  -7.750  -0.2018   0.08718   0.08371  -0.0499   0.9762   0.0223
  -7.500  -0.1945   0.08356   0.08012  -0.0521   0.9710   0.0221
  -7.000  -0.2089   0.06897   0.06557  -0.0613   0.9579   0.0189
  -6.750  -0.1989   0.06477   0.06140  -0.0651   0.9516   0.0187
  -6.500  -0.1897   0.05734   0.05396  -0.0731   0.9445   0.0183
  -6.250  -0.0985   0.03019   0.02547  -0.1338   0.9390   0.0170
  -6.000  -0.0397   0.02555   0.02017  -0.1450   0.9337   0.0170
  -5.750   0.0149   0.02267   0.01683  -0.1523   0.9288   0.0172
  -5.500   0.0585   0.02078   0.01464  -0.1564   0.9218   0.0175
  -5.250   0.0987   0.01929   0.01294  -0.1592   0.9128   0.0179
  -5.000   0.1360   0.01812   0.01162  -0.1613   0.9015   0.0184
  -4.750   0.1755   0.01706   0.01042  -0.1636   0.8857   0.0189
  -4.250   0.3606   0.01463   0.00680  -0.1898   0.6609   0.0238
  -4.000   0.3936   0.01454   0.00636  -0.1910   0.6113   0.0253
  -3.750   0.4254   0.01445   0.00595  -0.1919   0.5747   0.0275
  -3.500   0.4579   0.01430   0.00557  -0.1930   0.5463   0.0318
  -3.000   0.5340   0.01333   0.00490  -0.1984   0.5035   0.2111
  -2.750   0.5627   0.01353   0.00503  -0.1985   0.4878   0.2700
  -2.500   0.5907   0.01385   0.00525  -0.1983   0.4741   0.3057
  -2.250   0.6190   0.01405   0.00534  -0.1981   0.4626   0.3203
  -2.000   0.6475   0.01421   0.00531  -0.1980   0.4527   0.3286
  -1.750   0.6762   0.01429   0.00532  -0.1980   0.4432   0.3341
  -1.500   0.7048   0.01442   0.00532  -0.1979   0.4350   0.3397
  -1.250   0.7338   0.01451   0.00529  -0.1979   0.4267   0.3447
  -0.750   0.7911   0.01471   0.00537  -0.1979   0.4119   0.3532
  -0.500   0.8196   0.01485   0.00541  -0.1978   0.4051   0.3590
  -0.250   0.8482   0.01498   0.00548  -0.1978   0.3995   0.3641
   0.000   0.8770   0.01508   0.00558  -0.1978   0.3937   0.3691
   0.250   0.9054   0.01524   0.00567  -0.1977   0.3885   0.3753
   0.500   0.9337   0.01541   0.00578  -0.1976   0.3838   0.3815
   0.750   0.9624   0.01553   0.00593  -0.1976   0.3786   0.3884
   1.250   1.0190   0.01589   0.00623  -0.1975   0.3693   0.4056
   1.500   1.0475   0.01607   0.00642  -0.1974   0.3655   0.4154
   1.750   1.0762   0.01622   0.00662  -0.1974   0.3614   0.4258
   2.000   1.1044   0.01641   0.00682  -0.1974   0.3573   0.4373
   2.250   1.1325   0.01663   0.00704  -0.1973   0.3535   0.4505
   2.750   1.1892   0.01704   0.00755  -0.1972   0.3467   0.4833
   3.000   1.2175   0.01723   0.00784  -0.1972   0.3434   0.5027
   3.250   1.2456   0.01745   0.00811  -0.1971   0.3400   0.5243
   3.500   1.2734   0.01771   0.00840  -0.1970   0.3368   0.5483
   3.750   1.3012   0.01797   0.00873  -0.1968   0.3339   0.5747
   4.000   1.3291   0.01818   0.00908  -0.1967   0.3308   0.6053
   4.250   1.3563   0.01840   0.00945  -0.1964   0.3278   0.6413
   4.500   1.3825   0.01864   0.00981  -0.1959   0.3249   0.6839
   4.750   1.4080   0.01891   0.01016  -0.1952   0.3219   0.7251
   5.000   1.4339   0.01925   0.01049  -0.1947   0.3192   0.7582
   5.250   1.4601   0.01954   0.01086  -0.1942   0.3165   0.7848
   5.500   1.4853   0.01977   0.01123  -0.1936   0.3134   0.8081
   5.750   1.5091   0.01997   0.01154  -0.1926   0.3101   0.8333
   6.000   1.5277   0.02006   0.01176  -0.1905   0.3070   0.8818
   6.250   1.5503   0.02032   0.01204  -0.1893   0.3040   1.0000
   6.500   1.5766   0.02070   0.01246  -0.1890   0.3006   1.0000
   6.750   1.6025   0.02101   0.01288  -0.1886   0.2963   1.0000
   7.000   1.6279   0.02134   0.01328  -0.1881   0.2922   1.0000
   7.250   1.6529   0.02172   0.01365  -0.1876   0.2884   1.0000
   7.500   1.6779   0.02212   0.01411  -0.1870   0.2848   1.0000
   7.750   1.7026   0.02247   0.01461  -0.1864   0.2804   1.0000
   8.000   1.7266   0.02282   0.01504  -0.1857   0.2758   1.0000
   8.250   1.7499   0.02323   0.01545  -0.1848   0.2714   1.0000
   8.500   1.7732   0.02359   0.01597  -0.1840   0.2658   1.0000
   8.750   1.7957   0.02394   0.01642  -0.1830   0.2595   1.0000
   9.000   1.8172   0.02435   0.01688  -0.1818   0.2534   1.0000
   9.250   1.8389   0.02472   0.01739  -0.1807   0.2452   1.0000
   9.500   1.8592   0.02517   0.01790  -0.1794   0.2375   1.0000
   9.750   1.8792   0.02564   0.01846  -0.1781   0.2287   1.0000
  10.000   1.8986   0.02618   0.01909  -0.1766   0.2200   1.0000
  10.250   1.9156   0.02681   0.01978  -0.1749   0.2104   1.0000
  10.500   1.9316   0.02753   0.02056  -0.1729   0.1993   1.0000
  10.750   1.9445   0.02838   0.02146  -0.1705   0.1877   1.0000
  11.000   1.9546   0.02936   0.02247  -0.1677   0.1757   1.0000
  11.250   1.9622   0.03054   0.02367  -0.1647   0.1627   1.0000
  11.500   1.9679   0.03192   0.02507  -0.1615   0.1507   1.0000
  11.750   1.9712   0.03351   0.02669  -0.1582   0.1397   1.0000
  12.250   1.9738   0.03720   0.03050  -0.1516   0.1205   1.0000
  12.500   1.9718   0.03942   0.03279  -0.1484   0.1126   1.0000
  12.750   1.9674   0.04196   0.03542  -0.1453   0.1054   1.0000
  13.000   1.9626   0.04470   0.03827  -0.1426   0.0990   1.0000
  13.250   1.9535   0.04805   0.04172  -0.1402   0.0936   1.0000
  13.500   1.9436   0.05177   0.04560  -0.1384   0.0889   1.0000
  13.750   1.9312   0.05620   0.05018  -0.1374   0.0847   1.0000
  14.000   1.9138   0.06193   0.05607  -0.1378   0.0816   1.0000
  14.250   1.8966   0.06829   0.06261  -0.1391   0.0788   1.0000
  14.500   1.8784   0.07525   0.06976  -0.1411   0.0761   1.0000
  14.750   1.8570   0.08300   0.07768  -0.1436   0.0738   1.0000
  15.000   1.8342   0.09111   0.08595  -0.1463   0.0720   1.0000
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