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Ornithopter airfoil. (s1020-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: Ornithopter airfoil. (s1020-il)
Reynolds number: 200,000
Max Cl/Cd: 82.35 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1020-il-200000.txt
Download as CSV file: xf-s1020-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1807   0.09612   0.09271  -0.0889   0.9578   0.0641
  -9.000  -0.2059   0.08537   0.08202  -0.1080   0.9498   0.0680
  -8.750  -0.1996   0.08201   0.07869  -0.1049   0.9433   0.0692
  -8.500  -0.1743   0.08033   0.07698  -0.1042   0.9408   0.0705
  -8.250  -0.1541   0.07719   0.07383  -0.1070   0.9383   0.0725
  -8.000  -0.1537   0.07368   0.07034  -0.1090   0.9300   0.0749
  -7.000  -0.1986   0.03626   0.03098  -0.1372   0.8946   0.0423
  -6.750  -0.1938   0.03300   0.02677  -0.1342   0.8845   0.0370
  -6.500  -0.1609   0.03022   0.02361  -0.1362   0.8824   0.0370
  -6.250  -0.1252   0.02721   0.02027  -0.1387   0.8811   0.0374
  -6.000  -0.0851   0.02507   0.01786  -0.1414   0.8801   0.0374
  -5.750  -0.0710   0.02403   0.01670  -0.1390   0.8721   0.0375
  -5.500  -0.0359   0.02240   0.01498  -0.1405   0.8695   0.0381
  -5.250   0.0036   0.02099   0.01353  -0.1430   0.8677   0.0393
  -5.000   0.0447   0.01981   0.01232  -0.1457   0.8662   0.0414
  -4.750   0.0866   0.01878   0.01122  -0.1486   0.8647   0.0444
  -4.500   0.0996   0.01833   0.01076  -0.1460   0.8559   0.0477
  -4.250   0.1371   0.01751   0.00988  -0.1481   0.8529   0.0557
  -4.000   0.1762   0.01556   0.00854  -0.1514   0.8506   0.1744
  -3.750   0.2036   0.01479   0.00828  -0.1521   0.8455   0.3130
  -3.500   0.2296   0.01455   0.00829  -0.1520   0.8394   0.4050
  -3.250   0.2676   0.01434   0.00812  -0.1539   0.8362   0.4632
  -3.000   0.3079   0.01419   0.00793  -0.1562   0.8336   0.5052
  -2.750   0.3232   0.01441   0.00817  -0.1536   0.8250   0.5299
  -2.500   0.3586   0.01430   0.00801  -0.1549   0.8210   0.5544
  -2.250   0.3971   0.01417   0.00781  -0.1568   0.8179   0.5747
  -2.000   0.4135   0.01432   0.00797  -0.1545   0.8095   0.5897
  -1.750   0.4482   0.01420   0.00779  -0.1557   0.8053   0.6067
  -1.500   0.4764   0.01420   0.00776  -0.1557   0.7997   0.6217
  -1.250   0.5016   0.01422   0.00775  -0.1551   0.7931   0.6359
  -1.000   0.5368   0.01409   0.00757  -0.1565   0.7889   0.6508
  -0.750   0.5591   0.01418   0.00765  -0.1554   0.7819   0.6645
  -0.500   0.5881   0.01412   0.00757  -0.1556   0.7762   0.6779
  -0.250   0.6244   0.01400   0.00740  -0.1571   0.7723   0.6917
   0.000   0.6414   0.01412   0.00758  -0.1550   0.7641   0.7046
   0.250   0.6733   0.01403   0.00746  -0.1557   0.7590   0.7191
   0.500   0.6978   0.01408   0.00752  -0.1551   0.7526   0.7338
   0.750   0.7232   0.01407   0.00754  -0.1545   0.7462   0.7493
   1.000   0.7573   0.01398   0.00741  -0.1556   0.7418   0.7659
   1.250   0.7738   0.01408   0.00761  -0.1534   0.7336   0.7831
   1.500   0.8032   0.01401   0.00753  -0.1536   0.7283   0.8021
   1.750   0.8247   0.01406   0.00763  -0.1522   0.7216   0.8230
   2.000   0.8464   0.01401   0.00765  -0.1508   0.7150   0.8451
   2.250   0.8731   0.01394   0.00757  -0.1503   0.7099   0.8716
   2.500   0.8848   0.01392   0.00768  -0.1468   0.7020   0.9074
   3.000   0.9533   0.01391   0.00765  -0.1499   0.6888   1.0000
   3.250   0.9869   0.01397   0.00763  -0.1515   0.6827   1.0000
   3.500   1.0128   0.01416   0.00779  -0.1514   0.6754   1.0000
   3.750   1.0414   0.01427   0.00787  -0.1518   0.6685   1.0000
   4.000   1.0693   0.01443   0.00800  -0.1521   0.6619   1.0000
   4.250   1.0940   0.01459   0.00815  -0.1516   0.6543   1.0000
   4.500   1.1238   0.01472   0.00825  -0.1522   0.6478   1.0000
   4.750   1.1454   0.01491   0.00847  -0.1512   0.6397   1.0000
   5.000   1.1757   0.01504   0.00855  -0.1518   0.6331   1.0000
   5.250   1.1956   0.01525   0.00882  -0.1504   0.6245   1.0000
   5.500   1.2243   0.01539   0.00893  -0.1507   0.6174   1.0000
   5.750   1.2445   0.01559   0.00918  -0.1493   0.6087   1.0000
   6.000   1.2703   0.01578   0.00935  -0.1491   0.6011   1.0000
   6.250   1.2919   0.01597   0.00959  -0.1480   0.5924   1.0000
   6.500   1.3143   0.01619   0.00984  -0.1471   0.5842   1.0000
   6.750   1.3381   0.01637   0.01002  -0.1464   0.5756   1.0000
   7.000   1.3561   0.01663   0.01035  -0.1447   0.5664   1.0000
   7.250   1.3835   0.01680   0.01048  -0.1447   0.5579   1.0000
   7.500   1.3959   0.01707   0.01085  -0.1419   0.5477   1.0000
   7.750   1.4149   0.01732   0.01113  -0.1403   0.5381   1.0000
   8.000   1.4359   0.01753   0.01135  -0.1391   0.5283   1.0000
   8.250   1.4441   0.01783   0.01174  -0.1355   0.5176   1.0000
   8.500   1.4580   0.01812   0.01207  -0.1330   0.5069   1.0000
   8.750   1.4732   0.01842   0.01235  -0.1308   0.4957   1.0000
   9.000   1.4813   0.01878   0.01276  -0.1273   0.4832   1.0000
   9.250   1.4870   0.01921   0.01325  -0.1234   0.4696   1.0000
   9.500   1.4917   0.01970   0.01375  -0.1196   0.4543   1.0000
   9.750   1.4956   0.02028   0.01434  -0.1157   0.4381   1.0000
  10.000   1.4976   0.02100   0.01503  -0.1117   0.4203   1.0000
  10.250   1.4991   0.02185   0.01590  -0.1079   0.4024   1.0000
  10.500   1.5004   0.02283   0.01689  -0.1042   0.3835   1.0000
  10.750   1.5015   0.02395   0.01799  -0.1008   0.3645   1.0000
  11.000   1.5012   0.02525   0.01925  -0.0973   0.3449   1.0000
  11.250   1.5004   0.02670   0.02068  -0.0941   0.3234   1.0000
  11.500   1.4962   0.02846   0.02236  -0.0907   0.3011   1.0000
  11.750   1.4925   0.03035   0.02420  -0.0876   0.2777   1.0000
  12.000   1.4862   0.03257   0.02632  -0.0846   0.2549   1.0000
  12.250   1.4820   0.03481   0.02850  -0.0821   0.2328   1.0000
  12.500   1.4758   0.03734   0.03095  -0.0796   0.2125   1.0000
  12.750   1.4700   0.04000   0.03355  -0.0775   0.1896   1.0000
  13.000   1.4629   0.04291   0.03638  -0.0755   0.1697   1.0000
  13.250   1.4571   0.04587   0.03929  -0.0739   0.1483   1.0000
  13.750   1.4400   0.05277   0.04602  -0.0711   0.1063   1.0000
  14.000   1.4291   0.05672   0.04987  -0.0700   0.0845   1.0000
  14.250   1.4132   0.06141   0.05440  -0.0690   0.0614   1.0000
  14.500   1.3961   0.06649   0.05936  -0.0683   0.0459   1.0000
  14.750   1.3821   0.07143   0.06428  -0.0680   0.0378   1.0000
  15.000   1.3748   0.07567   0.06861  -0.0679   0.0331   1.0000
  15.250   1.3647   0.08038   0.07338  -0.0681   0.0309   1.0000
  15.500   1.3601   0.08445   0.07758  -0.0683   0.0290   1.0000
  15.750   1.3571   0.08835   0.08159  -0.0687   0.0275   1.0000
  16.000   1.3535   0.09240   0.08572  -0.0693   0.0260   1.0000
  16.250   1.3484   0.09664   0.09001  -0.0699   0.0250   1.0000
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