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S3010-103-84 (s3010-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S3010-103-84 (s3010-il)
Reynolds number: 100,000
Max Cl/Cd: 50.15 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3010-il-100000.txt
Download as CSV file: xf-s3010-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3010-103-84                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3942   0.09905   0.09425  -0.0162   1.0000   0.1090
  -8.500  -0.4026   0.09628   0.09158  -0.0203   1.0000   0.1136
  -8.250  -0.4322   0.09386   0.08935  -0.0288   1.0000   0.1149
  -8.000  -0.3897   0.08894   0.08433  -0.0213   1.0000   0.1195
  -7.750  -0.3847   0.08598   0.08143  -0.0221   1.0000   0.1241
  -7.500  -0.4122   0.08292   0.07853  -0.0315   1.0000   0.1291
  -7.250  -0.4033   0.07868   0.07436  -0.0301   1.0000   0.1317
  -7.000  -0.3887   0.07608   0.07179  -0.0273   1.0000   0.1356
  -6.750  -0.4179   0.07169   0.06736  -0.0401   1.0000   0.1450
  -6.500  -0.4015   0.06855   0.06439  -0.0348   1.0000   0.1468
  -6.250  -0.3959   0.06648   0.06239  -0.0315   1.0000   0.1501
  -5.750  -0.4173   0.06126   0.05717  -0.0314   1.0000   0.1622
  -5.500  -0.4163   0.05936   0.05534  -0.0284   1.0000   0.1652
  -5.250  -0.4107   0.04251   0.03700  -0.0402   1.0000   0.0852
  -5.000  -0.3969   0.03641   0.03027  -0.0402   1.0000   0.0707
  -4.750  -0.3809   0.03291   0.02638  -0.0398   1.0000   0.0669
  -4.500  -0.3395   0.02849   0.02083  -0.0427   0.9947   0.0624
  -4.250  -0.2972   0.02632   0.01845  -0.0462   0.9871   0.0653
  -4.000  -0.2534   0.02444   0.01622  -0.0493   0.9793   0.0684
  -3.750  -0.2069   0.02264   0.01406  -0.0525   0.9722   0.0715
  -3.500  -0.1665   0.02101   0.01238  -0.0547   0.9631   0.0770
  -3.250  -0.1224   0.01979   0.01125  -0.0578   0.9551   0.0941
  -3.000  -0.0811   0.01818   0.00999  -0.0603   0.9462   0.1512
  -2.750  -0.0432   0.01683   0.00949  -0.0628   0.9364   0.3082
  -2.500  -0.0004   0.01586   0.00931  -0.0655   0.9289   0.4849
  -2.250   0.0288   0.01535   0.00931  -0.0649   0.9169   0.6258
  -2.000   0.0561   0.01504   0.00935  -0.0632   0.9056   0.7509
  -1.750   0.0909   0.01477   0.00924  -0.0620   0.8976   0.8666
  -1.500   0.1606   0.01450   0.00881  -0.0683   0.8892   0.9645
  -1.250   0.2315   0.01412   0.00813  -0.0762   0.8817   1.0000
  -1.000   0.2510   0.01415   0.00796  -0.0748   0.8661   1.0000
  -0.750   0.2720   0.01419   0.00781  -0.0733   0.8516   1.0000
  -0.500   0.2927   0.01427   0.00773  -0.0717   0.8367   1.0000
  -0.250   0.3142   0.01436   0.00766  -0.0702   0.8220   1.0000
   0.000   0.3366   0.01446   0.00761  -0.0687   0.8076   1.0000
   0.250   0.3597   0.01455   0.00756  -0.0674   0.7932   1.0000
   0.500   0.3833   0.01464   0.00753  -0.0661   0.7790   1.0000
   0.750   0.4074   0.01473   0.00749  -0.0649   0.7650   1.0000
   1.000   0.4319   0.01482   0.00746  -0.0638   0.7511   1.0000
   1.250   0.4567   0.01490   0.00744  -0.0627   0.7373   1.0000
   1.500   0.4819   0.01499   0.00742  -0.0616   0.7235   1.0000
   1.750   0.5074   0.01508   0.00739  -0.0606   0.7099   1.0000
   2.000   0.5330   0.01517   0.00737  -0.0597   0.6961   1.0000
   2.250   0.5585   0.01531   0.00744  -0.0588   0.6812   1.0000
   2.500   0.5841   0.01545   0.00750  -0.0580   0.6662   1.0000
   2.750   0.6098   0.01560   0.00758  -0.0572   0.6511   1.0000
   3.000   0.6357   0.01576   0.00768  -0.0564   0.6359   1.0000
   3.250   0.6615   0.01594   0.00780  -0.0557   0.6206   1.0000
   3.500   0.6874   0.01613   0.00792  -0.0550   0.6052   1.0000
   3.750   0.7133   0.01633   0.00806  -0.0543   0.5897   1.0000
   4.000   0.7393   0.01654   0.00824  -0.0536   0.5740   1.0000
   4.250   0.7651   0.01677   0.00841  -0.0530   0.5581   1.0000
   4.500   0.7909   0.01702   0.00859  -0.0523   0.5419   1.0000
   4.750   0.8162   0.01730   0.00887  -0.0516   0.5247   1.0000
   5.000   0.8414   0.01760   0.00917  -0.0510   0.5072   1.0000
   5.250   0.8666   0.01790   0.00946  -0.0503   0.4896   1.0000
   5.500   0.8917   0.01822   0.00975  -0.0496   0.4721   1.0000
   5.750   0.9167   0.01855   0.01005  -0.0490   0.4544   1.0000
   6.000   0.9417   0.01891   0.01036  -0.0483   0.4370   1.0000
   6.250   0.9663   0.01931   0.01070  -0.0476   0.4192   1.0000
   6.500   0.9900   0.01976   0.01119  -0.0469   0.4002   1.0000
   6.750   1.0136   0.02021   0.01167  -0.0461   0.3814   1.0000
   7.000   1.0372   0.02069   0.01211  -0.0454   0.3632   1.0000
   7.250   1.0607   0.02120   0.01256  -0.0446   0.3453   1.0000
   7.500   1.0831   0.02179   0.01318  -0.0438   0.3269   1.0000
   7.750   1.1050   0.02241   0.01385  -0.0430   0.3083   1.0000
   8.000   1.1267   0.02307   0.01450  -0.0421   0.2903   1.0000
   8.250   1.1481   0.02379   0.01518  -0.0412   0.2731   1.0000
   8.500   1.1692   0.02457   0.01593  -0.0404   0.2564   1.0000
   8.750   1.1899   0.02546   0.01676  -0.0395   0.2404   1.0000
   9.000   1.2091   0.02638   0.01773  -0.0385   0.2246   1.0000
   9.250   1.2281   0.02738   0.01876  -0.0374   0.2097   1.0000
   9.500   1.2467   0.02843   0.01984  -0.0364   0.1956   1.0000
   9.750   1.2657   0.02958   0.02094  -0.0355   0.1826   1.0000
  10.000   1.2820   0.03071   0.02221  -0.0342   0.1702   1.0000
  10.250   1.2976   0.03204   0.02368  -0.0329   0.1589   1.0000
  10.500   1.3135   0.03350   0.02526  -0.0317   0.1487   1.0000
  10.750   1.3315   0.03497   0.02667  -0.0308   0.1393   1.0000
  11.000   1.3444   0.03643   0.02831  -0.0293   0.1307   1.0000
  11.250   1.3575   0.03826   0.03029  -0.0280   0.1230   1.0000
  11.500   1.3744   0.03975   0.03170  -0.0271   0.1152   1.0000
  11.750   1.3791   0.04185   0.03416  -0.0250   0.1091   1.0000
  12.000   1.3977   0.04354   0.03565  -0.0246   0.1013   1.0000
  12.250   1.3900   0.04542   0.03801  -0.0214   0.0970   1.0000
  12.500   1.3913   0.04674   0.03937  -0.0192   0.0914   1.0000
  12.750   1.3908   0.04904   0.04179  -0.0174   0.0866   1.0000
  13.000   1.3801   0.05139   0.04442  -0.0152   0.0829   1.0000
  13.250   1.3921   0.05326   0.04607  -0.0146   0.0766   1.0000
  13.500   1.3743   0.05653   0.04975  -0.0132   0.0747   1.0000
  13.750   1.3597   0.06008   0.05359  -0.0126   0.0720   1.0000
  14.000   1.3524   0.06327   0.05692  -0.0126   0.0689   1.0000
  14.250   1.3537   0.06649   0.06009  -0.0125   0.0649   1.0000
  14.500   1.3317   0.07173   0.06567  -0.0137   0.0640   1.0000
  14.750   1.3083   0.07769   0.07194  -0.0157   0.0633   1.0000
  15.000   1.2832   0.08445   0.07898  -0.0187   0.0631   1.0000
  15.250   1.2544   0.09233   0.08711  -0.0228   0.0632   1.0000
  15.500   1.2235   0.10135   0.09636  -0.0280   0.0639   1.0000
  15.750   1.1913   0.11151   0.10670  -0.0341   0.0649   1.0000
  16.000   1.1581   0.12286   0.11818  -0.0411   0.0657   1.0000
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