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S1221 w/ 4 deg flap (s1221-flap-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S1221 w/ 4 deg flap (s1221-flap-il)
Reynolds number: 100,000
Max Cl/Cd: 56.39 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1221-flap-il-100000-n5.txt
Download as CSV file: xf-s1221-flap-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.1982   0.08708   0.08290  -0.0298   0.9925   0.0372
  -7.250  -0.1853   0.08211   0.07794  -0.0334   0.9877   0.0352
  -6.750  -0.3033   0.08815   0.08382  -0.0253   0.9969   0.0323
  -6.500  -0.2828   0.08477   0.08044  -0.0292   0.9910   0.0317
  -6.250  -0.2634   0.08014   0.07583  -0.0350   0.9841   0.0308
  -5.750  -0.2208   0.05272   0.04817  -0.0747   0.9672   0.0268
  -5.500  -0.1166   0.03630   0.03050  -0.1164   0.9632   0.0262
  -5.250  -0.0431   0.03095   0.02431  -0.1307   0.9583   0.0266
  -5.000   0.0137   0.02813   0.02104  -0.1384   0.9514   0.0282
  -4.750   0.0646   0.02623   0.01893  -0.1438   0.9431   0.0301
  -4.500   0.1086   0.02445   0.01691  -0.1471   0.9323   0.0311
  -4.250   0.1516   0.02298   0.01528  -0.1499   0.9203   0.0321
  -4.000   0.1917   0.02175   0.01405  -0.1521   0.9048   0.0335
  -3.750   0.2273   0.02081   0.01311  -0.1536   0.8813   0.0354
  -3.500   0.2553   0.02016   0.01238  -0.1537   0.8352   0.0381
  -3.000   0.4751   0.01638   0.00804  -0.1864   0.6572   0.2889
  -2.750   0.5074   0.01721   0.00857  -0.1867   0.6139   0.3322
  -2.500   0.5384   0.01761   0.00868  -0.1870   0.5826   0.3505
  -2.250   0.5717   0.01781   0.00850  -0.1879   0.5584   0.3622
  -2.000   0.6020   0.01794   0.00845  -0.1881   0.5392   0.3691
  -1.750   0.6340   0.01806   0.00830  -0.1887   0.5225   0.3770
  -1.500   0.6650   0.01817   0.00821  -0.1892   0.5078   0.3832
  -1.250   0.6954   0.01827   0.00816  -0.1895   0.4949   0.3890
  -1.000   0.7267   0.01841   0.00808  -0.1901   0.4837   0.3958
  -0.750   0.7561   0.01855   0.00811  -0.1902   0.4738   0.4016
  -0.500   0.7859   0.01870   0.00816  -0.1904   0.4650   0.4082
  -0.250   0.8159   0.01887   0.00819  -0.1908   0.4568   0.4150
   0.000   0.8451   0.01904   0.00830  -0.1908   0.4492   0.4214
   0.250   0.8747   0.01923   0.00840  -0.1911   0.4415   0.4303
   0.500   0.9037   0.01946   0.00856  -0.1912   0.4351   0.4383
   0.750   0.9334   0.01965   0.00872  -0.1914   0.4282   0.4484
   1.000   0.9622   0.01987   0.00892  -0.1914   0.4226   0.4573
   1.250   0.9913   0.02014   0.00913  -0.1916   0.4176   0.4684
   1.500   1.0202   0.02037   0.00940  -0.1916   0.4117   0.4815
   1.750   1.0485   0.02062   0.00965  -0.1916   0.4064   0.4954
   2.250   1.1050   0.02118   0.01026  -0.1915   0.3971   0.5290
   2.500   1.1332   0.02146   0.01061  -0.1914   0.3925   0.5488
   2.750   1.1609   0.02176   0.01094  -0.1912   0.3884   0.5716
   3.000   1.1885   0.02210   0.01128  -0.1910   0.3847   0.5991
   3.250   1.2149   0.02238   0.01178  -0.1906   0.3801   0.6298
   3.500   1.2407   0.02270   0.01223  -0.1899   0.3760   0.6646
   3.750   1.2663   0.02304   0.01265  -0.1893   0.3725   0.7048
   4.000   1.2921   0.02341   0.01305  -0.1887   0.3693   0.7462
   4.250   1.3179   0.02379   0.01352  -0.1881   0.3656   0.7859
   4.500   1.3407   0.02406   0.01395  -0.1869   0.3616   0.8228
   4.750   1.3576   0.02417   0.01422  -0.1844   0.3583   0.8808
   5.000   1.3826   0.02452   0.01462  -0.1838   0.3552   1.0000
   5.250   1.4115   0.02505   0.01507  -0.1841   0.3522   1.0000
   5.500   1.4386   0.02560   0.01572  -0.1840   0.3484   1.0000
   5.750   1.4651   0.02616   0.01640  -0.1838   0.3444   1.0000
   6.000   1.4919   0.02670   0.01700  -0.1836   0.3408   1.0000
   6.250   1.5188   0.02722   0.01752  -0.1835   0.3374   1.0000
   6.500   1.5457   0.02777   0.01809  -0.1833   0.3341   1.0000
   6.750   1.5695   0.02841   0.01894  -0.1827   0.3296   1.0000
   7.000   1.5942   0.02897   0.01962  -0.1822   0.3253   1.0000
   7.250   1.6196   0.02947   0.02016  -0.1817   0.3214   1.0000
   7.500   1.6449   0.03000   0.02072  -0.1813   0.3176   1.0000
   7.750   1.6663   0.03068   0.02166  -0.1802   0.3123   1.0000
   8.000   1.6895   0.03121   0.02231  -0.1794   0.3075   1.0000
   8.250   1.7142   0.03164   0.02274  -0.1789   0.3035   1.0000
   8.500   1.7346   0.03237   0.02370  -0.1777   0.2984   1.0000
   8.750   1.7552   0.03299   0.02452  -0.1765   0.2929   1.0000
   9.000   1.7779   0.03340   0.02497  -0.1756   0.2882   1.0000
   9.250   1.7964   0.03409   0.02587  -0.1741   0.2824   1.0000
   9.500   1.8144   0.03468   0.02664  -0.1725   0.2759   1.0000
   9.750   1.8346   0.03501   0.02699  -0.1711   0.2703   1.0000
  10.000   1.8478   0.03586   0.02819  -0.1689   0.2625   1.0000
  10.250   1.8643   0.03627   0.02866  -0.1670   0.2560   1.0000
  10.500   1.8757   0.03717   0.02985  -0.1646   0.2477   1.0000
  10.750   1.8882   0.03771   0.03047  -0.1621   0.2405   1.0000
  11.000   1.8954   0.03879   0.03184  -0.1591   0.2313   1.0000
  11.250   1.9006   0.03972   0.03288  -0.1557   0.2236   1.0000
  11.500   1.9039   0.04092   0.03427  -0.1523   0.2146   1.0000
  11.750   1.9058   0.04233   0.03584  -0.1490   0.2057   1.0000
  12.000   1.9051   0.04392   0.03751  -0.1456   0.1973   1.0000
  12.250   1.9025   0.04602   0.03980  -0.1425   0.1876   1.0000
  12.500   1.8967   0.04846   0.04237  -0.1395   0.1790   1.0000
  12.750   1.8871   0.05146   0.04547  -0.1367   0.1708   1.0000
  13.000   1.8747   0.05512   0.04930  -0.1346   0.1629   1.0000
  13.250   1.8566   0.05975   0.05402  -0.1332   0.1565   1.0000
  13.500   1.8359   0.06548   0.05996  -0.1332   0.1505   1.0000
  13.750   1.8100   0.07273   0.06737  -0.1347   0.1457   1.0000
  14.000   1.7813   0.08113   0.07591  -0.1374   0.1415   1.0000
  14.250   1.7513   0.09035   0.08533  -0.1408   0.1369   1.0000
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