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SA7038 (sa7038-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: SA7038 (sa7038-il)
Reynolds number: 500,000
Max Cl/Cd: 92.52 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7038-il-500000-n5.txt
Download as CSV file: xf-sa7038-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7038                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3678   0.08345   0.08126  -0.0354   1.0000   0.0094
  -8.250  -0.3750   0.08058   0.07844  -0.0349   1.0000   0.0092
  -8.000  -0.3662   0.07567   0.07355  -0.0401   0.9936   0.0089
  -7.750  -0.3555   0.06981   0.06769  -0.0477   0.9856   0.0086
  -7.500  -0.3387   0.06173   0.05960  -0.0605   0.9775   0.0086
  -7.250  -0.3187   0.05061   0.04834  -0.0766   0.9687   0.0083
  -7.000  -0.3073   0.03911   0.03650  -0.0862   0.9573   0.0083
  -6.750  -0.3009   0.03000   0.02681  -0.0888   0.9458   0.0083
  -6.500  -0.2867   0.02472   0.02097  -0.0892   0.9377   0.0084
  -6.250  -0.2668   0.02184   0.01767  -0.0889   0.9309   0.0087
  -6.000  -0.2446   0.01982   0.01528  -0.0884   0.9246   0.0091
  -5.750  -0.2213   0.01815   0.01328  -0.0879   0.9178   0.0093
  -5.500  -0.1973   0.01655   0.01138  -0.0874   0.9116   0.0093
  -5.250  -0.1726   0.01526   0.00984  -0.0869   0.9043   0.0093
  -5.000  -0.1472   0.01418   0.00855  -0.0864   0.8981   0.0093
  -4.750  -0.1215   0.01327   0.00748  -0.0859   0.8909   0.0094
  -4.500  -0.0954   0.01250   0.00656  -0.0855   0.8845   0.0095
  -4.250  -0.0692   0.01184   0.00579  -0.0851   0.8767   0.0097
  -4.000  -0.0427   0.01130   0.00515  -0.0847   0.8690   0.0099
  -3.750  -0.0163   0.01075   0.00451  -0.0844   0.8601   0.0101
  -3.500   0.0101   0.01011   0.00376  -0.0841   0.8506   0.0107
  -3.250   0.0370   0.00974   0.00331  -0.0838   0.8410   0.0113
  -3.000   0.0642   0.00945   0.00294  -0.0835   0.8306   0.0119
  -2.750   0.0915   0.00922   0.00264  -0.0833   0.8196   0.0127
  -2.500   0.1189   0.00904   0.00239  -0.0831   0.8081   0.0139
  -2.250   0.1464   0.00888   0.00213  -0.0828   0.7959   0.0145
  -2.000   0.1738   0.00873   0.00190  -0.0826   0.7822   0.0167
  -1.750   0.2010   0.00852   0.00171  -0.0823   0.7669   0.0347
  -1.500   0.2278   0.00826   0.00155  -0.0821   0.7503   0.0872
  -1.250   0.2547   0.00805   0.00145  -0.0820   0.7338   0.1426
  -1.000   0.2814   0.00780   0.00138  -0.0819   0.7173   0.2209
  -0.750   0.3074   0.00734   0.00136  -0.0818   0.7007   0.3808
  -0.500   0.3333   0.00699   0.00136  -0.0816   0.6837   0.5187
  -0.250   0.3594   0.00682   0.00137  -0.0812   0.6660   0.6053
   0.000   0.3853   0.00672   0.00139  -0.0808   0.6480   0.6754
   0.250   0.4104   0.00663   0.00142  -0.0801   0.6296   0.7456
   0.500   0.4342   0.00654   0.00147  -0.0790   0.6105   0.8182
   0.750   0.4555   0.00647   0.00151  -0.0771   0.5922   0.8978
   1.000   0.4906   0.00650   0.00150  -0.0785   0.5724   0.9791
   1.250   0.5211   0.00663   0.00152  -0.0791   0.5534   1.0000
   1.500   0.5476   0.00679   0.00156  -0.0788   0.5347   1.0000
   1.750   0.5741   0.00696   0.00162  -0.0785   0.5165   1.0000
   2.000   0.6006   0.00712   0.00169  -0.0783   0.4980   1.0000
   2.250   0.6270   0.00730   0.00177  -0.0780   0.4788   1.0000
   2.500   0.6533   0.00750   0.00187  -0.0777   0.4595   1.0000
   2.750   0.6797   0.00769   0.00197  -0.0774   0.4399   1.0000
   3.000   0.7059   0.00790   0.00209  -0.0772   0.4206   1.0000
   3.250   0.7321   0.00811   0.00222  -0.0769   0.4026   1.0000
   3.500   0.7584   0.00832   0.00235  -0.0767   0.3858   1.0000
   3.750   0.7845   0.00854   0.00250  -0.0764   0.3677   1.0000
   4.000   0.8104   0.00879   0.00268  -0.0761   0.3486   1.0000
   4.250   0.8361   0.00905   0.00286  -0.0758   0.3282   1.0000
   4.500   0.8617   0.00932   0.00304  -0.0755   0.3088   1.0000
   4.750   0.8873   0.00959   0.00325  -0.0751   0.2921   1.0000
   5.000   0.9127   0.00987   0.00348  -0.0748   0.2749   1.0000
   5.250   0.9382   0.01015   0.00371  -0.0745   0.2589   1.0000
   5.500   0.9636   0.01043   0.00395  -0.0741   0.2442   1.0000
   5.750   0.9886   0.01074   0.00420  -0.0737   0.2275   1.0000
   6.000   1.0135   0.01106   0.00449  -0.0733   0.2124   1.0000
   6.250   1.0379   0.01143   0.00480  -0.0729   0.1952   1.0000
   6.500   1.0619   0.01183   0.00512  -0.0724   0.1773   1.0000
   6.750   1.0861   0.01220   0.00545  -0.0719   0.1626   1.0000
   7.000   1.1099   0.01260   0.00582  -0.0714   0.1470   1.0000
   7.250   1.1334   0.01302   0.00620  -0.0708   0.1327   1.0000
   7.500   1.1564   0.01348   0.00661  -0.0701   0.1171   1.0000
   7.750   1.1783   0.01404   0.00707  -0.0694   0.0992   1.0000
   8.000   1.2001   0.01458   0.00755  -0.0686   0.0832   1.0000
   8.250   1.2219   0.01510   0.00805  -0.0678   0.0716   1.0000
   8.500   1.2430   0.01567   0.00858  -0.0670   0.0595   1.0000
   8.750   1.2633   0.01631   0.00916  -0.0660   0.0469   1.0000
   9.000   1.2827   0.01698   0.00979  -0.0649   0.0362   1.0000
   9.250   1.3022   0.01762   0.01041  -0.0638   0.0294   1.0000
   9.500   1.3213   0.01826   0.01106  -0.0627   0.0238   1.0000
   9.750   1.3396   0.01893   0.01174  -0.0614   0.0186   1.0000
  10.000   1.3565   0.01967   0.01252  -0.0600   0.0138   1.0000
  10.250   1.3714   0.02052   0.01337  -0.0583   0.0087   1.0000
  10.500   1.3840   0.02138   0.01426  -0.0562   0.0060   1.0000
  10.750   1.3945   0.02228   0.01522  -0.0538   0.0047   1.0000
  11.000   1.4063   0.02310   0.01613  -0.0516   0.0043   1.0000
  11.250   1.4173   0.02398   0.01711  -0.0495   0.0041   1.0000
  11.500   1.4265   0.02501   0.01824  -0.0473   0.0037   1.0000
  11.750   1.4354   0.02609   0.01941  -0.0452   0.0035   1.0000
  12.000   1.4420   0.02736   0.02080  -0.0430   0.0033   1.0000
  12.250   1.4485   0.02869   0.02226  -0.0411   0.0032   1.0000
  12.500   1.4514   0.03036   0.02406  -0.0390   0.0029   1.0000
  12.750   1.4560   0.03196   0.02578  -0.0373   0.0028   1.0000
  13.000   1.4597   0.03371   0.02766  -0.0357   0.0028   1.0000
  13.250   1.4623   0.03566   0.02973  -0.0344   0.0027   1.0000
  13.500   1.4620   0.03799   0.03221  -0.0333   0.0027   1.0000
  13.750   1.4616   0.04049   0.03484  -0.0324   0.0026   1.0000
  14.000   1.4598   0.04329   0.03778  -0.0319   0.0026   1.0000
  14.250   1.4571   0.04637   0.04100  -0.0318   0.0026   1.0000
  14.500   1.4510   0.05008   0.04487  -0.0321   0.0025   1.0000
  14.750   1.4452   0.05396   0.04889  -0.0328   0.0025   1.0000
  15.000   1.4375   0.05835   0.05343  -0.0339   0.0025   1.0000
  15.250   1.4279   0.06329   0.05853  -0.0356   0.0024   1.0000
  15.500   1.4169   0.06871   0.06410  -0.0377   0.0024   1.0000
  15.750   1.4061   0.07438   0.06992  -0.0401   0.0024   1.0000
  16.000   1.3910   0.08104   0.07674  -0.0431   0.0024   1.0000
  16.250   1.3782   0.08753   0.08339  -0.0462   0.0024   1.0000
  16.500   1.3625   0.09482   0.09083  -0.0499   0.0023   1.0000
  16.750   1.3463   0.10239   0.09855  -0.0537   0.0024   1.0000
  17.000   1.3306   0.11009   0.10639  -0.0578   0.0024   1.0000
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