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S7055 (10.5%) Flat-Bottomed (s7055-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S7055 (10.5%) Flat-Bottomed (s7055-il)
Reynolds number: 100,000
Max Cl/Cd: 54.29 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s7055-il-100000.txt
Download as CSV file: xf-s7055-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S7055 (10.5%) Flat-Bottomed                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3315   0.10372   0.09896  -0.0376   1.0000   0.0804
  -9.000  -0.3236   0.10063   0.09590  -0.0370   1.0000   0.0835
  -8.750  -0.3227   0.09789   0.09322  -0.0376   1.0000   0.0866
  -8.500  -0.3287   0.09553   0.09096  -0.0389   1.0000   0.0893
  -8.250  -0.3495   0.09424   0.08984  -0.0406   1.0000   0.0909
  -8.000  -0.3723   0.09331   0.08907  -0.0393   1.0000   0.0911
  -7.750  -0.3986   0.09256   0.08844  -0.0369   1.0000   0.0913
  -7.500  -0.4239   0.09138   0.08737  -0.0363   1.0000   0.0915
  -7.250  -0.4464   0.08988   0.08586  -0.0364   1.0000   0.0917
  -7.000  -0.4202   0.08507   0.08116  -0.0275   1.0000   0.0948
  -6.750  -0.4282   0.08325   0.07940  -0.0249   1.0000   0.0966
  -6.500  -0.4008   0.07384   0.07029  -0.0314   0.9937   0.1055
  -6.250  -0.3789   0.06886   0.06538  -0.0283   0.9900   0.1096
  -6.000  -0.3709   0.06307   0.05938  -0.0405   0.9804   0.1197
  -5.750  -0.4367   0.07105   0.06720  -0.0299   0.9945   0.1102
  -5.500  -0.4097   0.06557   0.06148  -0.0390   0.9860   0.1222
  -5.250  -0.3838   0.06150   0.05723  -0.0440   0.9786   0.1362
  -5.000  -0.3553   0.05762   0.05322  -0.0480   0.9717   0.1508
  -4.750  -0.3309   0.05419   0.04968  -0.0505   0.9640   0.1655
  -4.500  -0.3010   0.05082   0.04624  -0.0529   0.9577   0.1819
  -4.250  -0.2592   0.03926   0.03306  -0.0590   0.9503   0.0940
  -4.000  -0.2238   0.03504   0.02829  -0.0607   0.9445   0.0842
  -3.750  -0.1896   0.03208   0.02422  -0.0609   0.9374   0.0780
  -3.500  -0.1549   0.02907   0.02076  -0.0622   0.9312   0.0788
  -3.250  -0.1189   0.02744   0.01901  -0.0639   0.9250   0.0871
  -3.000  -0.0846   0.02586   0.01700  -0.0646   0.9175   0.0931
  -2.750  -0.0387   0.02451   0.01548  -0.0678   0.9133   0.1072
  -2.500  -0.0133   0.02380   0.01473  -0.0673   0.9035   0.1194
  -2.250   0.0325   0.02251   0.01353  -0.0704   0.8994   0.1362
  -2.000   0.0557   0.02191   0.01309  -0.0696   0.8894   0.1581
  -1.750   0.1947   0.01771   0.01179  -0.0889   0.9002   1.0000
  -1.500   0.2200   0.01783   0.01161  -0.0886   0.8892   1.0000
  -1.250   0.2535   0.01785   0.01137  -0.0897   0.8806   1.0000
  -1.000   0.2890   0.01780   0.01110  -0.0910   0.8725   1.0000
  -0.750   0.3127   0.01794   0.01106  -0.0901   0.8616   1.0000
  -0.500   0.3476   0.01786   0.01081  -0.0911   0.8543   1.0000
  -0.250   0.3730   0.01793   0.01074  -0.0904   0.8440   1.0000
   0.000   0.3952   0.01809   0.01078  -0.0892   0.8331   1.0000
   0.250   0.4259   0.01802   0.01057  -0.0893   0.8253   1.0000
   0.500   0.4503   0.01808   0.01054  -0.0883   0.8151   1.0000
   0.750   0.4718   0.01825   0.01062  -0.0869   0.8042   1.0000
   1.000   0.4988   0.01823   0.01051  -0.0862   0.7954   1.0000
   1.250   0.5251   0.01820   0.01041  -0.0854   0.7861   1.0000
   1.500   0.5467   0.01836   0.01052  -0.0840   0.7749   1.0000
   1.750   0.5718   0.01839   0.01049  -0.0831   0.7652   1.0000
   2.000   0.6004   0.01823   0.01027  -0.0825   0.7568   1.0000
   2.250   0.6224   0.01838   0.01039  -0.0811   0.7451   1.0000
   2.500   0.6463   0.01846   0.01044  -0.0800   0.7343   1.0000
   2.750   0.6745   0.01832   0.01027  -0.0794   0.7254   1.0000
   3.000   0.6998   0.01832   0.01024  -0.0784   0.7147   1.0000
   3.250   0.7231   0.01845   0.01037  -0.0773   0.7027   1.0000
   3.500   0.7475   0.01853   0.01045  -0.0763   0.6912   1.0000
   3.750   0.7736   0.01854   0.01046  -0.0755   0.6803   1.0000
   4.000   0.8025   0.01841   0.01029  -0.0749   0.6704   1.0000
   4.250   0.8261   0.01855   0.01045  -0.0739   0.6574   1.0000
   4.500   0.8502   0.01867   0.01058  -0.0728   0.6443   1.0000
   4.750   0.8746   0.01879   0.01074  -0.0719   0.6311   1.0000
   5.000   0.8992   0.01891   0.01088  -0.0709   0.6178   1.0000
   5.250   0.9238   0.01905   0.01104  -0.0700   0.6042   1.0000
   5.500   0.9484   0.01919   0.01121  -0.0690   0.5902   1.0000
   5.750   0.9728   0.01935   0.01143  -0.0681   0.5759   1.0000
   6.000   0.9971   0.01952   0.01162  -0.0671   0.5611   1.0000
   6.250   1.0213   0.01969   0.01182  -0.0661   0.5458   1.0000
   6.500   1.0454   0.01987   0.01201  -0.0652   0.5300   1.0000
   6.750   1.0698   0.02006   0.01223  -0.0642   0.5138   1.0000
   7.000   1.0910   0.02037   0.01261  -0.0628   0.4961   1.0000
   7.250   1.1120   0.02067   0.01297  -0.0615   0.4776   1.0000
   7.500   1.1340   0.02094   0.01325  -0.0602   0.4590   1.0000
   7.750   1.1547   0.02127   0.01363  -0.0588   0.4396   1.0000
   8.000   1.1731   0.02165   0.01408  -0.0571   0.4187   1.0000
   8.250   1.1926   0.02204   0.01445  -0.0555   0.3980   1.0000
   8.500   1.2081   0.02252   0.01502  -0.0534   0.3755   1.0000
   8.750   1.2235   0.02303   0.01553  -0.0513   0.3530   1.0000
   9.000   1.2368   0.02359   0.01609  -0.0490   0.3293   1.0000
   9.250   1.2467   0.02425   0.01683  -0.0463   0.3043   1.0000
   9.500   1.2546   0.02501   0.01759  -0.0433   0.2793   1.0000
   9.750   1.2598   0.02589   0.01843  -0.0401   0.2545   1.0000
  10.000   1.2615   0.02692   0.01938  -0.0365   0.2303   1.0000
  10.250   1.2588   0.02807   0.02053  -0.0325   0.2063   1.0000
  10.500   1.2551   0.02952   0.02191  -0.0288   0.1828   1.0000
  10.750   1.2493   0.03130   0.02352  -0.0254   0.1606   1.0000
  11.000   1.2428   0.03334   0.02554  -0.0224   0.1374   1.0000
  11.250   1.2349   0.03576   0.02784  -0.0197   0.1162   1.0000
  11.500   1.2271   0.03837   0.03037  -0.0175   0.0984   1.0000
  11.750   1.2186   0.04132   0.03316  -0.0156   0.0835   1.0000
  12.000   1.2120   0.04436   0.03611  -0.0140   0.0707   1.0000
  12.250   1.2086   0.04727   0.03913  -0.0127   0.0608   1.0000
  12.500   1.2078   0.05018   0.04213  -0.0114   0.0526   1.0000
  12.750   1.2119   0.05301   0.04487  -0.0101   0.0466   1.0000
  13.000   1.2200   0.05561   0.04769  -0.0088   0.0427   1.0000
  13.250   1.2292   0.05820   0.05031  -0.0078   0.0396   1.0000
  13.500   1.2435   0.06157   0.05376  -0.0066   0.0369   1.0000
  13.750   1.2426   0.06490   0.05741  -0.0060   0.0360   1.0000
  14.000   1.2361   0.06858   0.06139  -0.0058   0.0346   1.0000
  14.250   1.2298   0.07263   0.06571  -0.0059   0.0337   1.0000
  14.500   1.2213   0.07701   0.07034  -0.0063   0.0332   1.0000
  14.750   1.2094   0.08191   0.07550  -0.0072   0.0328   1.0000
  15.000   1.1943   0.08741   0.08128  -0.0087   0.0330   1.0000
  15.250   1.1760   0.09355   0.08769  -0.0110   0.0330   1.0000
  15.500   1.1554   0.10039   0.09478  -0.0142   0.0331   1.0000
  15.750   1.1332   0.10798   0.10260  -0.0182   0.0335   1.0000
  16.000   1.1091   0.11651   0.11135  -0.0232   0.0341   1.0000
  16.250   1.0838   0.12604   0.12106  -0.0290   0.0351   1.0000
  16.500   1.0596   0.13607   0.13123  -0.0354   0.0360   1.0000
  16.750   1.0378   0.14635   0.14158  -0.0416   0.0369   1.0000
  17.000   1.0220   0.15575   0.15100  -0.0469   0.0376   1.0000
  17.250   0.9666   0.18434   0.17949  -0.0628   0.0474   1.0000
  17.500   0.7421   0.19522   0.19093  -0.0634   0.1078   1.0000
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