Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S7055 (10.5%) Flat-Bottomed (s7055-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S7055 (10.5%) Flat-Bottomed (s7055-il)
Reynolds number: 200,000
Max Cl/Cd: 75.44 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s7055-il-200000-n5.txt
Download as CSV file: xf-s7055-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3412   0.08844   0.08508  -0.0408   1.0000   0.0149
  -8.750  -0.3445   0.08497   0.08167  -0.0417   1.0000   0.0152
  -8.500  -0.3511   0.08166   0.07845  -0.0422   1.0000   0.0151
  -8.250  -0.3552   0.07760   0.07446  -0.0445   0.9924   0.0150
  -8.000  -0.3432   0.07195   0.06880  -0.0526   0.9783   0.0161
  -7.750  -0.3317   0.06446   0.06130  -0.0637   0.9625   0.0164
  -7.500  -0.3203   0.05591   0.05260  -0.0741   0.9488   0.0165
  -7.250  -0.3124   0.04764   0.04406  -0.0806   0.9357   0.0163
  -7.000  -0.3075   0.03996   0.03595  -0.0833   0.9235   0.0163
  -6.750  -0.3030   0.03278   0.02813  -0.0835   0.9127   0.0165
  -6.500  -0.2934   0.02789   0.02257  -0.0822   0.9024   0.0169
  -6.250  -0.2774   0.02449   0.01855  -0.0809   0.8941   0.0175
  -6.000  -0.2562   0.02252   0.01604  -0.0799   0.8868   0.0185
  -5.750  -0.2345   0.02129   0.01467  -0.0793   0.8792   0.0198
  -5.500  -0.2108   0.02026   0.01342  -0.0786   0.8724   0.0208
  -5.250  -0.1872   0.01904   0.01195  -0.0778   0.8651   0.0218
  -5.000  -0.1627   0.01792   0.01059  -0.0771   0.8584   0.0231
  -4.750  -0.1381   0.01694   0.00940  -0.0763   0.8511   0.0247
  -4.500  -0.1135   0.01600   0.00828  -0.0755   0.8443   0.0266
  -4.250  -0.0886   0.01550   0.00775  -0.0750   0.8368   0.0298
  -4.000  -0.0628   0.01508   0.00719  -0.0745   0.8298   0.0342
  -3.750  -0.0384   0.01440   0.00646  -0.0738   0.8218   0.0381
  -3.500  -0.0126   0.01403   0.00601  -0.0733   0.8148   0.0433
  -3.250   0.0128   0.01369   0.00558  -0.0728   0.8065   0.0495
  -3.000   0.0387   0.01336   0.00520  -0.0723   0.7998   0.0562
  -2.750   0.0643   0.01304   0.00481  -0.0718   0.7911   0.0615
  -2.500   0.0901   0.01271   0.00445  -0.0713   0.7840   0.0699
  -2.250   0.1159   0.01241   0.00411  -0.0709   0.7755   0.0798
  -2.000   0.1419   0.01213   0.00384  -0.0704   0.7677   0.0988
  -1.750   0.1673   0.01178   0.00361  -0.0700   0.7595   0.1420
  -1.500   0.1914   0.01126   0.00346  -0.0695   0.7509   0.2475
  -1.250   0.2148   0.01075   0.00331  -0.0688   0.7430   0.3770
  -1.000   0.2366   0.01022   0.00325  -0.0676   0.7338   0.5166
  -0.750   0.2551   0.00955   0.00325  -0.0653   0.7253   0.7174
  -0.500   0.3191   0.00919   0.00327  -0.0717   0.7169   0.9443
  -0.250   0.3793   0.00920   0.00314  -0.0783   0.7073   0.9903
   0.000   0.4171   0.00923   0.00302  -0.0805   0.6978   1.0000
   0.250   0.4408   0.00928   0.00295  -0.0797   0.6882   1.0000
   0.500   0.4647   0.00934   0.00292  -0.0789   0.6779   1.0000
   0.750   0.4887   0.00942   0.00290  -0.0781   0.6682   1.0000
   1.000   0.5128   0.00950   0.00287  -0.0773   0.6583   1.0000
   1.250   0.5369   0.00959   0.00288  -0.0766   0.6476   1.0000
   1.500   0.5610   0.00968   0.00291  -0.0758   0.6369   1.0000
   1.750   0.5852   0.00979   0.00294  -0.0751   0.6263   1.0000
   2.000   0.6094   0.00991   0.00298  -0.0743   0.6155   1.0000
   2.250   0.6336   0.01004   0.00304  -0.0736   0.6041   1.0000
   2.500   0.6577   0.01016   0.00312  -0.0728   0.5926   1.0000
   2.750   0.6819   0.01030   0.00322  -0.0721   0.5814   1.0000
   3.000   0.7060   0.01045   0.00332  -0.0714   0.5700   1.0000
   3.250   0.7300   0.01061   0.00343  -0.0706   0.5586   1.0000
   3.500   0.7539   0.01078   0.00355  -0.0698   0.5464   1.0000
   3.750   0.7778   0.01096   0.00371  -0.0691   0.5336   1.0000
   4.000   0.8016   0.01114   0.00387  -0.0683   0.5204   1.0000
   4.250   0.8253   0.01134   0.00404  -0.0676   0.5072   1.0000
   4.500   0.8490   0.01155   0.00423  -0.0668   0.4942   1.0000
   4.750   0.8725   0.01176   0.00445  -0.0660   0.4811   1.0000
   5.000   0.8959   0.01200   0.00467  -0.0652   0.4679   1.0000
   5.250   0.9190   0.01224   0.00490  -0.0644   0.4539   1.0000
   5.500   0.9419   0.01251   0.00515  -0.0636   0.4394   1.0000
   5.750   0.9645   0.01279   0.00542  -0.0627   0.4245   1.0000
   6.000   0.9868   0.01308   0.00573  -0.0617   0.4091   1.0000
   6.250   1.0087   0.01340   0.00604  -0.0608   0.3934   1.0000
   6.500   1.0302   0.01374   0.00637  -0.0598   0.3775   1.0000
   6.750   1.0513   0.01410   0.00672  -0.0587   0.3606   1.0000
   7.000   1.0720   0.01448   0.00713  -0.0576   0.3422   1.0000
   7.250   1.0917   0.01491   0.00753  -0.0563   0.3236   1.0000
   7.500   1.1108   0.01537   0.00797  -0.0550   0.3048   1.0000
   7.750   1.1296   0.01584   0.00844  -0.0536   0.2850   1.0000
   8.000   1.1469   0.01638   0.00895  -0.0521   0.2653   1.0000
   8.250   1.1636   0.01695   0.00950  -0.0505   0.2440   1.0000
   8.500   1.1780   0.01762   0.01013  -0.0486   0.2212   1.0000
   8.750   1.1920   0.01831   0.01078  -0.0466   0.1985   1.0000
   9.000   1.2042   0.01906   0.01147  -0.0444   0.1773   1.0000
   9.250   1.2123   0.01991   0.01223  -0.0417   0.1548   1.0000
   9.500   1.2192   0.02086   0.01308  -0.0388   0.1300   1.0000
   9.750   1.2249   0.02195   0.01405  -0.0361   0.1062   1.0000
  10.000   1.2292   0.02321   0.01517  -0.0334   0.0827   1.0000
  10.250   1.2333   0.02454   0.01640  -0.0309   0.0640   1.0000
  10.500   1.2375   0.02594   0.01775  -0.0286   0.0475   1.0000
  10.750   1.2415   0.02741   0.01918  -0.0265   0.0351   1.0000
  11.000   1.2446   0.02903   0.02079  -0.0244   0.0254   1.0000
  11.250   1.2486   0.03065   0.02244  -0.0227   0.0194   1.0000
  11.500   1.2510   0.03249   0.02434  -0.0209   0.0151   1.0000
  11.750   1.2523   0.03450   0.02641  -0.0193   0.0122   1.0000
  12.000   1.2528   0.03667   0.02870  -0.0179   0.0107   1.0000
  12.250   1.2552   0.03875   0.03093  -0.0168   0.0099   1.0000
  12.500   1.2559   0.04107   0.03339  -0.0159   0.0091   1.0000
  12.750   1.2548   0.04368   0.03612  -0.0151   0.0084   1.0000
  13.000   1.2502   0.04677   0.03934  -0.0145   0.0079   1.0000
  13.250   1.2460   0.04995   0.04265  -0.0143   0.0077   1.0000
  13.500   1.2435   0.05306   0.04595  -0.0142   0.0075   1.0000
  13.750   1.2392   0.05653   0.04959  -0.0143   0.0073   1.0000
  14.000   1.2353   0.06008   0.05329  -0.0147   0.0072   1.0000
  14.250   1.2308   0.06385   0.05721  -0.0153   0.0070   1.0000
  14.500   1.2253   0.06790   0.06141  -0.0161   0.0069   1.0000
  14.750   1.2196   0.07211   0.06577  -0.0171   0.0068   1.0000
  15.000   1.2143   0.07637   0.07018  -0.0183   0.0067   1.0000
  15.250   1.2086   0.08081   0.07476  -0.0196   0.0066   1.0000
  15.500   1.2030   0.08536   0.07944  -0.0210   0.0065   1.0000
  15.750   1.1969   0.09009   0.08432  -0.0226   0.0064   1.0000
  16.000   1.1915   0.09482   0.08918  -0.0244   0.0063   1.0000
  16.250   1.1859   0.09970   0.09420  -0.0263   0.0062   1.0000
  16.500   1.1796   0.10483   0.09946  -0.0285   0.0060   1.0000
  16.750   1.1736   0.11002   0.10479  -0.0308   0.0059   1.0000
  17.000   1.1672   0.11535   0.11025  -0.0333   0.0058   1.0000
  17.250   1.1601   0.12103   0.11603  -0.0363   0.0056   1.0000
  17.500   1.1541   0.12642   0.12157  -0.0387   0.0056   1.0000
  17.750   1.1472   0.13225   0.12750  -0.0419   0.0054   1.0000
  18.000   1.1407   0.13800   0.13337  -0.0450   0.0054   1.0000
  18.250   1.1343   0.14387   0.13937  -0.0482   0.0054   1.0000
  18.500   1.1272   0.15002   0.14563  -0.0517   0.0053   1.0000
  18.750   1.1195   0.15646   0.15219  -0.0554   0.0052   1.0000
  19.000   1.1120   0.16302   0.15887  -0.0593   0.0052   1.0000
  19.250   1.1050   0.16975   0.16573  -0.0634   0.0052   1.0000
<< Back to S7055 (10.5%) Flat-Bottomed (s7055-il)

Polar data table (+)

Polar graphs


<< Back to S7055 (10.5%) Flat-Bottomed (s7055-il)