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Ornithopter airfoil. (s1020-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: Ornithopter airfoil. (s1020-il)
Reynolds number: 500,000
Max Cl/Cd: 111.15 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1020-il-500000-n5.txt
Download as CSV file: xf-s1020-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.1776   0.09846   0.09591  -0.1007   0.9705   0.0111
 -11.250  -0.3312   0.05307   0.05025  -0.1268   0.9519   0.0099
 -10.750  -0.3691   0.03692   0.03352  -0.1445   0.9288   0.0098
 -10.500  -0.3667   0.03178   0.02803  -0.1522   0.9186   0.0098
 -10.250  -0.3487   0.02826   0.02414  -0.1577   0.9104   0.0100
 -10.000  -0.3292   0.02585   0.02142  -0.1604   0.9015   0.0101
  -9.500  -0.2857   0.02231   0.01733  -0.1633   0.8841   0.0104
  -9.250  -0.2633   0.02101   0.01580  -0.1639   0.8760   0.0106
  -9.000  -0.2422   0.01992   0.01450  -0.1639   0.8673   0.0108
  -8.750  -0.2203   0.01900   0.01340  -0.1638   0.8596   0.0110
  -8.500  -0.1983   0.01815   0.01238  -0.1635   0.8516   0.0111
  -8.250  -0.1760   0.01741   0.01150  -0.1632   0.8446   0.0113
  -8.000  -0.1532   0.01679   0.01074  -0.1628   0.8373   0.0114
  -7.750  -0.1297   0.01621   0.01003  -0.1626   0.8308   0.0115
  -7.500  -0.1085   0.01541   0.00914  -0.1619   0.8237   0.0117
  -7.250  -0.0857   0.01469   0.00832  -0.1616   0.8176   0.0120
  -7.000  -0.0631   0.01416   0.00773  -0.1611   0.8110   0.0123
  -6.750  -0.0389   0.01369   0.00719  -0.1608   0.8048   0.0127
  -6.500  -0.0144   0.01331   0.00676  -0.1605   0.7990   0.0132
  -6.250   0.0100   0.01292   0.00630  -0.1602   0.7928   0.0136
  -6.000   0.0356   0.01256   0.00584  -0.1601   0.7873   0.0140
  -5.750   0.0602   0.01220   0.00542  -0.1597   0.7814   0.0144
  -5.500   0.0857   0.01189   0.00503  -0.1595   0.7755   0.0148
  -5.250   0.1118   0.01163   0.00469  -0.1594   0.7702   0.0151
  -5.000   0.1371   0.01127   0.00428  -0.1592   0.7643   0.0159
  -4.750   0.1633   0.01104   0.00398  -0.1590   0.7587   0.0168
  -4.500   0.1897   0.01084   0.00373  -0.1589   0.7534   0.0177
  -4.250   0.2159   0.01067   0.00350  -0.1587   0.7475   0.0191
  -4.000   0.2425   0.01047   0.00327  -0.1586   0.7421   0.0229
  -3.750   0.2685   0.01017   0.00305  -0.1585   0.7365   0.0451
  -3.500   0.2945   0.00987   0.00286  -0.1585   0.7306   0.0807
  -3.000   0.3470   0.00930   0.00256  -0.1585   0.7194   0.1770
  -2.750   0.3731   0.00900   0.00245  -0.1585   0.7135   0.2427
  -2.500   0.3994   0.00872   0.00237  -0.1586   0.7080   0.3150
  -2.250   0.4258   0.00856   0.00234  -0.1585   0.7020   0.3710
  -2.000   0.4523   0.00848   0.00234  -0.1584   0.6962   0.4197
  -1.750   0.4791   0.00844   0.00234  -0.1583   0.6904   0.4469
  -1.500   0.5056   0.00844   0.00233  -0.1581   0.6842   0.4623
  -1.250   0.5322   0.00846   0.00233  -0.1579   0.6785   0.4771
  -1.000   0.5588   0.00847   0.00234  -0.1577   0.6722   0.4901
  -0.750   0.5850   0.00851   0.00234  -0.1574   0.6661   0.5024
  -0.500   0.6115   0.00853   0.00236  -0.1572   0.6601   0.5146
  -0.250   0.6376   0.00856   0.00238  -0.1570   0.6538   0.5258
   0.000   0.6636   0.00861   0.00241  -0.1567   0.6478   0.5363
   0.250   0.6896   0.00864   0.00245  -0.1564   0.6411   0.5469
   0.500   0.7151   0.00871   0.00249  -0.1560   0.6350   0.5571
   0.750   0.7411   0.00875   0.00254  -0.1557   0.6284   0.5682
   1.000   0.7662   0.00881   0.00260  -0.1552   0.6217   0.5796
   1.250   0.7917   0.00887   0.00267  -0.1548   0.6155   0.5909
   1.500   0.8167   0.00893   0.00274  -0.1543   0.6084   0.6026
   1.750   0.8414   0.00901   0.00282  -0.1538   0.6020   0.6151
   2.000   0.8662   0.00908   0.00292  -0.1533   0.5948   0.6276
   2.250   0.8901   0.00917   0.00301  -0.1526   0.5881   0.6403
   2.500   0.9144   0.00924   0.00311  -0.1520   0.5809   0.6538
   2.750   0.9370   0.00934   0.00323  -0.1510   0.5739   0.6675
   3.000   0.9606   0.00942   0.00334  -0.1502   0.5668   0.6822
   3.250   0.9827   0.00952   0.00347  -0.1492   0.5597   0.6978
   3.500   1.0056   0.00961   0.00360  -0.1483   0.5527   0.7142
   3.750   1.0272   0.00973   0.00376  -0.1471   0.5451   0.7312
   4.000   1.0493   0.00984   0.00392  -0.1461   0.5379   0.7504
   4.250   1.0703   0.00998   0.00410  -0.1448   0.5299   0.7714
   4.500   1.0915   0.01010   0.00429  -0.1436   0.5222   0.7938
   4.750   1.1107   0.01024   0.00448  -0.1420   0.5139   0.8203
   5.000   1.1296   0.01033   0.00467  -0.1402   0.5061   0.8552
   5.250   1.1437   0.01038   0.00484  -0.1374   0.4982   0.9239
   5.500   1.1693   0.01052   0.00501  -0.1372   0.4895   1.0000
   5.750   1.1894   0.01078   0.00524  -0.1360   0.4812   1.0000
   6.000   1.2109   0.01100   0.00546  -0.1349   0.4723   1.0000
   6.250   1.2306   0.01127   0.00572  -0.1336   0.4638   1.0000
   6.500   1.2500   0.01155   0.00600  -0.1323   0.4535   1.0000
   6.750   1.2694   0.01185   0.00628  -0.1309   0.4430   1.0000
   7.000   1.2874   0.01218   0.00660  -0.1294   0.4330   1.0000
   7.250   1.3043   0.01256   0.00695  -0.1276   0.4212   1.0000
   7.500   1.3214   0.01295   0.00733  -0.1259   0.4081   1.0000
   8.000   1.3465   0.01406   0.00831  -0.1212   0.3700   1.0000
   8.250   1.3558   0.01479   0.00894  -0.1184   0.3469   1.0000
   8.500   1.3646   0.01559   0.00965  -0.1156   0.3231   1.0000
   8.750   1.3704   0.01656   0.01049  -0.1125   0.2964   1.0000
   9.000   1.3750   0.01766   0.01145  -0.1093   0.2686   1.0000
   9.250   1.3786   0.01888   0.01252  -0.1062   0.2404   1.0000
   9.500   1.3821   0.02016   0.01367  -0.1032   0.2138   1.0000
   9.750   1.3857   0.02151   0.01490  -0.1004   0.1882   1.0000
  10.000   1.3904   0.02285   0.01615  -0.0978   0.1676   1.0000
  10.250   1.3945   0.02428   0.01749  -0.0953   0.1464   1.0000
  10.500   1.3980   0.02582   0.01894  -0.0929   0.1272   1.0000
  10.750   1.4017   0.02740   0.02045  -0.0907   0.1090   1.0000
  11.000   1.4037   0.02917   0.02213  -0.0884   0.0912   1.0000
  11.250   1.4071   0.03091   0.02382  -0.0864   0.0766   1.0000
  11.500   1.4089   0.03284   0.02568  -0.0844   0.0612   1.0000
  11.750   1.4108   0.03484   0.02764  -0.0826   0.0485   1.0000
  12.000   1.4122   0.03695   0.02972  -0.0808   0.0374   1.0000
  12.250   1.4154   0.03899   0.03174  -0.0794   0.0291   1.0000
  12.500   1.4171   0.04122   0.03396  -0.0779   0.0207   1.0000
  12.750   1.4174   0.04366   0.03639  -0.0766   0.0136   1.0000
  13.000   1.4200   0.04596   0.03872  -0.0754   0.0106   1.0000
  13.250   1.4238   0.04821   0.04103  -0.0745   0.0092   1.0000
  13.500   1.4294   0.05033   0.04322  -0.0738   0.0086   1.0000
  13.750   1.4343   0.05256   0.04554  -0.0730   0.0081   1.0000
  14.000   1.4390   0.05487   0.04792  -0.0724   0.0078   1.0000
  14.250   1.4425   0.05738   0.05052  -0.0719   0.0074   1.0000
  14.500   1.4452   0.06003   0.05325  -0.0715   0.0071   1.0000
  14.750   1.4472   0.06283   0.05613  -0.0711   0.0069   1.0000
  15.000   1.4494   0.06565   0.05904  -0.0708   0.0066   1.0000
  15.250   1.4519   0.06849   0.06198  -0.0707   0.0065   1.0000
  15.500   1.4538   0.07147   0.06506  -0.0707   0.0064   1.0000
  15.750   1.4553   0.07456   0.06826  -0.0707   0.0063   1.0000
  16.000   1.4558   0.07784   0.07164  -0.0709   0.0062   1.0000
  16.250   1.4560   0.08118   0.07508  -0.0712   0.0060   1.0000
  16.500   1.4553   0.08474   0.07874  -0.0716   0.0060   1.0000
  16.750   1.4542   0.08842   0.08252  -0.0721   0.0058   1.0000
  17.000   1.4526   0.09222   0.08643  -0.0728   0.0057   1.0000
  17.250   1.4506   0.09613   0.09044  -0.0736   0.0056   1.0000
  17.500   1.4482   0.10013   0.09454  -0.0745   0.0055   1.0000
  17.750   1.4455   0.10424   0.09875  -0.0755   0.0054   1.0000
  18.000   1.4418   0.10855   0.10317  -0.0768   0.0053   1.0000
  18.250   1.4380   0.11293   0.10764  -0.0781   0.0052   1.0000
  18.500   1.4335   0.11745   0.11227  -0.0797   0.0052   1.0000
  18.750   1.4283   0.12212   0.11705  -0.0814   0.0051   1.0000
  19.000   1.4224   0.12695   0.12197  -0.0832   0.0050   1.0000
  19.250   1.4171   0.13169   0.12681  -0.0852   0.0049   1.0000
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