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Ornithopter airfoil. (s1020-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: Ornithopter airfoil. (s1020-il)
Reynolds number: 500,000
Max Cl/Cd: 120 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1020-il-500000.txt
Download as CSV file: xf-s1020-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Ornithopter airfoil.                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.0460   0.09623   0.09394  -0.1038   0.9653   0.0271
 -11.250  -0.0422   0.09119   0.08890  -0.1070   0.9640   0.0286
 -10.000  -0.1442   0.07746   0.07513  -0.1173   0.9634   0.0306
  -9.750  -0.1278   0.07419   0.07186  -0.1211   0.9620   0.0311
  -9.500  -0.1221   0.07149   0.06916  -0.1221   0.9536   0.0316
  -9.250  -0.1114   0.06640   0.06407  -0.1278   0.9507   0.0325
  -9.000  -0.1400   0.05114   0.04872  -0.1447   0.9392   0.0327
  -8.750  -0.1071   0.02821   0.02520  -0.1602   0.9128   0.0367
  -8.500  -0.1276   0.02101   0.01758  -0.1623   0.9003   0.0377
  -8.250  -0.1053   0.01828   0.01483  -0.1641   0.8948   0.0386
  -8.000  -0.1455   0.02111   0.01585  -0.1655   0.8965   0.0196
  -7.750  -0.1191   0.01988   0.01440  -0.1660   0.8901   0.0194
  -7.500  -0.0942   0.01860   0.01295  -0.1660   0.8830   0.0194
  -7.250  -0.0661   0.01722   0.01139  -0.1668   0.8774   0.0195
  -7.000  -0.0451   0.01608   0.01015  -0.1659   0.8697   0.0197
  -6.750  -0.0166   0.01506   0.00900  -0.1665   0.8642   0.0198
  -6.500   0.0041   0.01433   0.00823  -0.1655   0.8568   0.0202
  -6.250   0.0304   0.01369   0.00752  -0.1656   0.8508   0.0206
  -6.000   0.0549   0.01323   0.00701  -0.1653   0.8445   0.0214
  -5.750   0.0795   0.01276   0.00648  -0.1649   0.8380   0.0222
  -5.500   0.1072   0.01229   0.00591  -0.1652   0.8326   0.0229
  -5.250   0.1303   0.01189   0.00546  -0.1644   0.8259   0.0235
  -5.000   0.1574   0.01149   0.00497  -0.1645   0.8203   0.0243
  -4.750   0.1829   0.01107   0.00448  -0.1643   0.8145   0.0260
  -4.500   0.2086   0.01080   0.00417  -0.1640   0.8083   0.0280
  -4.250   0.2378   0.01053   0.00382  -0.1644   0.8032   0.0328
  -4.000   0.2612   0.00996   0.00349  -0.1640   0.7970   0.0836
  -3.750   0.2866   0.00934   0.00322  -0.1641   0.7912   0.1856
  -3.500   0.3138   0.00891   0.00305  -0.1645   0.7860   0.2754
  -3.250   0.3388   0.00863   0.00297  -0.1642   0.7798   0.3435
  -3.000   0.3666   0.00849   0.00292  -0.1644   0.7744   0.3967
  -2.750   0.3937   0.00844   0.00291  -0.1643   0.7688   0.4355
  -2.500   0.4200   0.00840   0.00290  -0.1641   0.7627   0.4621
  -2.250   0.4490   0.00842   0.00287  -0.1644   0.7575   0.4859
  -2.000   0.4746   0.00841   0.00290  -0.1639   0.7514   0.5079
  -1.750   0.5016   0.00841   0.00288  -0.1638   0.7456   0.5230
  -1.500   0.5300   0.00845   0.00286  -0.1639   0.7402   0.5365
  -1.250   0.5555   0.00845   0.00287  -0.1635   0.7339   0.5492
  -1.000   0.5831   0.00846   0.00286  -0.1635   0.7282   0.5609
  -0.750   0.6096   0.00848   0.00287  -0.1633   0.7222   0.5727
  -0.500   0.6359   0.00849   0.00288  -0.1630   0.7160   0.5848
  -0.250   0.6641   0.00854   0.00288  -0.1631   0.7105   0.5968
   0.000   0.6888   0.00853   0.00292  -0.1625   0.7038   0.6079
   0.250   0.7158   0.00857   0.00293  -0.1624   0.6978   0.6198
   0.500   0.7420   0.00861   0.00298  -0.1621   0.6916   0.6324
   0.750   0.7675   0.00863   0.00302  -0.1617   0.6849   0.6454
   1.000   0.7944   0.00869   0.00307  -0.1616   0.6790   0.6588
   1.250   0.8189   0.00871   0.00314  -0.1610   0.6721   0.6727
   1.500   0.8455   0.00877   0.00318  -0.1608   0.6658   0.6876
   1.750   0.8698   0.00880   0.00328  -0.1601   0.6589   0.7032
   2.000   0.8951   0.00886   0.00334  -0.1597   0.6521   0.7197
   2.250   0.9197   0.00891   0.00344  -0.1591   0.6454   0.7372
   2.500   0.9439   0.00896   0.00353  -0.1584   0.6383   0.7560
   2.750   0.9684   0.00903   0.00363  -0.1578   0.6317   0.7759
   3.000   0.9911   0.00907   0.00374  -0.1568   0.6243   0.7972
   3.250   1.0146   0.00915   0.00385  -0.1559   0.6177   0.8215
   3.500   1.0351   0.00917   0.00398  -0.1544   0.6102   0.8493
   3.750   1.0551   0.00923   0.00407  -0.1527   0.6034   0.8846
   4.000   1.0742   0.00914   0.00414  -0.1508   0.5958   0.9638
   4.250   1.1010   0.00930   0.00423  -0.1508   0.5884   1.0000
   4.500   1.1235   0.00942   0.00437  -0.1499   0.5803   1.0000
   4.750   1.1465   0.00961   0.00450  -0.1491   0.5728   1.0000
   5.000   1.1676   0.00973   0.00465  -0.1479   0.5648   1.0000
   5.250   1.1896   0.00994   0.00481  -0.1469   0.5572   1.0000
   5.500   1.2102   0.01009   0.00499  -0.1456   0.5490   1.0000
   5.750   1.2314   0.01031   0.00517  -0.1445   0.5414   1.0000
   6.000   1.2516   0.01049   0.00537  -0.1432   0.5328   1.0000
   6.250   1.2719   0.01072   0.00559  -0.1419   0.5248   1.0000
   6.500   1.2912   0.01094   0.00582  -0.1404   0.5157   1.0000
   6.750   1.3108   0.01117   0.00606  -0.1390   0.5070   1.0000
   7.000   1.3292   0.01145   0.00631  -0.1374   0.4980   1.0000
   7.250   1.3469   0.01170   0.00660  -0.1357   0.4874   1.0000
   7.500   1.3641   0.01200   0.00690  -0.1339   0.4769   1.0000
   7.750   1.3785   0.01237   0.00723  -0.1316   0.4633   1.0000
   8.000   1.3921   0.01277   0.00761  -0.1292   0.4491   1.0000
   8.250   1.4058   0.01320   0.00802  -0.1269   0.4345   1.0000
   8.500   1.4185   0.01369   0.00848  -0.1245   0.4187   1.0000
   8.750   1.4296   0.01425   0.00901  -0.1219   0.3996   1.0000
   9.000   1.4397   0.01491   0.00961  -0.1191   0.3805   1.0000
   9.250   1.4468   0.01571   0.01033  -0.1161   0.3597   1.0000
   9.500   1.4551   0.01653   0.01110  -0.1133   0.3377   1.0000
   9.750   1.4596   0.01758   0.01205  -0.1101   0.3142   1.0000
  10.000   1.4650   0.01866   0.01304  -0.1072   0.2906   1.0000
  10.250   1.4679   0.01993   0.01420  -0.1041   0.2664   1.0000
  10.500   1.4694   0.02136   0.01551  -0.1009   0.2419   1.0000
  10.750   1.4714   0.02284   0.01689  -0.0981   0.2174   1.0000
  11.000   1.4717   0.02450   0.01843  -0.0952   0.1934   1.0000
  11.500   1.4710   0.02818   0.02190  -0.0898   0.1468   1.0000
  11.750   1.4701   0.03020   0.02381  -0.0874   0.1259   1.0000
  12.000   1.4672   0.03246   0.02596  -0.0849   0.1039   1.0000
  12.250   1.4646   0.03479   0.02819  -0.0827   0.0836   1.0000
  12.500   1.4601   0.03740   0.03069  -0.0806   0.0642   1.0000
  12.750   1.4520   0.04047   0.03363  -0.0784   0.0432   1.0000
  13.000   1.4434   0.04371   0.03677  -0.0765   0.0266   1.0000
  13.250   1.4391   0.04672   0.03975  -0.0750   0.0186   1.0000
  13.500   1.4399   0.04931   0.04238  -0.0740   0.0158   1.0000
  13.750   1.4418   0.05185   0.04501  -0.0731   0.0144   1.0000
  14.000   1.4449   0.05433   0.04757  -0.0724   0.0136   1.0000
  14.250   1.4461   0.05709   0.05041  -0.0717   0.0128   1.0000
  14.500   1.4451   0.06018   0.05359  -0.0712   0.0122   1.0000
  14.750   1.4431   0.06349   0.05699  -0.0707   0.0118   1.0000
  15.000   1.4444   0.06646   0.06007  -0.0705   0.0115   1.0000
  15.250   1.4445   0.06964   0.06335  -0.0703   0.0113   1.0000
  15.500   1.4438   0.07301   0.06682  -0.0703   0.0110   1.0000
  15.750   1.4429   0.07647   0.07039  -0.0705   0.0108   1.0000
  16.000   1.4407   0.08018   0.07420  -0.0707   0.0105   1.0000
  16.250   1.4386   0.08393   0.07805  -0.0711   0.0103   1.0000
  16.500   1.4355   0.08789   0.08212  -0.0717   0.0102   1.0000
  16.750   1.4323   0.09193   0.08625  -0.0723   0.0099   1.0000
  17.000   1.4282   0.09617   0.09058  -0.0732   0.0097   1.0000
  17.250   1.4228   0.10063   0.09513  -0.0741   0.0096   1.0000
  17.500   1.4156   0.10541   0.10001  -0.0753   0.0094   1.0000
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