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SA7038 (sa7038-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: SA7038 (sa7038-il)
Reynolds number: 1,000,000
Max Cl/Cd: 119.28 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7038-il-1000000.txt
Download as CSV file: xf-sa7038-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3647   0.09988   0.09822  -0.0317   1.0000   0.0093
  -9.500  -0.3623   0.09637   0.09473  -0.0328   1.0000   0.0093
  -8.000  -0.3699   0.07529   0.07381  -0.0396   0.9971   0.0100
  -7.750  -0.3554   0.07034   0.06886  -0.0466   0.9917   0.0102
  -7.500  -0.3351   0.06400   0.06251  -0.0574   0.9866   0.0103
  -7.250  -0.3071   0.05614   0.05460  -0.0716   0.9837   0.0107
  -7.000  -0.2858   0.04752   0.04585  -0.0830   0.9753   0.0109
  -6.750  -0.2687   0.04025   0.03836  -0.0892   0.9661   0.0113
  -6.500  -0.2571   0.03430   0.03214  -0.0910   0.9561   0.0118
  -6.250  -0.2389   0.03043   0.02791  -0.0904   0.9471   0.0132
  -6.000  -0.2231   0.02728   0.02439  -0.0900   0.9394   0.0133
  -5.750  -0.2195   0.00809   0.00488  -0.0835   0.9162   0.0144
  -5.500  -0.1966   0.00723   0.00393  -0.0834   0.9102   0.0150
  -5.250  -0.1731   0.00636   0.00289  -0.0832   0.9040   0.0163
  -5.000  -0.1452   0.01423   0.00986  -0.0874   0.9124   0.0125
  -4.750  -0.1202   0.01255   0.00793  -0.0868   0.9056   0.0120
  -4.500  -0.0945   0.01158   0.00679  -0.0863   0.8994   0.0121
  -4.250  -0.0680   0.01077   0.00587  -0.0859   0.8920   0.0123
  -4.000  -0.0420   0.00989   0.00485  -0.0853   0.8855   0.0121
  -3.750  -0.0152   0.00919   0.00407  -0.0850   0.8776   0.0121
  -3.500   0.0116   0.00868   0.00345  -0.0846   0.8705   0.0123
  -3.250   0.0390   0.00827   0.00298  -0.0844   0.8618   0.0128
  -3.000   0.0665   0.00800   0.00264  -0.0842   0.8534   0.0133
  -2.750   0.0938   0.00759   0.00211  -0.0839   0.8438   0.0142
  -2.500   0.1215   0.00736   0.00181  -0.0837   0.8329   0.0153
  -2.250   0.1493   0.00720   0.00159  -0.0835   0.8216   0.0168
  -2.000   0.1770   0.00705   0.00140  -0.0833   0.8099   0.0217
  -1.750   0.2041   0.00662   0.00121  -0.0832   0.7975   0.0982
  -1.250   0.2585   0.00606   0.00104  -0.0831   0.7698   0.2574
  -1.000   0.2856   0.00583   0.00099  -0.0831   0.7543   0.3419
  -0.750   0.3125   0.00556   0.00097  -0.0830   0.7377   0.4496
  -0.500   0.3388   0.00525   0.00098  -0.0828   0.7199   0.5845
  -0.250   0.3648   0.00505   0.00101  -0.0824   0.7019   0.6917
   0.000   0.3906   0.00491   0.00104  -0.0818   0.6840   0.7735
   0.250   0.4145   0.00478   0.00108  -0.0808   0.6660   0.8568
   0.500   0.4357   0.00470   0.00111  -0.0789   0.6486   0.9359
   1.000   0.5027   0.00486   0.00110  -0.0812   0.6109   1.0000
   1.250   0.5296   0.00499   0.00114  -0.0810   0.5915   1.0000
   1.750   0.5834   0.00528   0.00122  -0.0806   0.5531   1.0000
   2.000   0.6103   0.00544   0.00129  -0.0804   0.5324   1.0000
   2.250   0.6372   0.00560   0.00135  -0.0802   0.5132   1.0000
   2.500   0.6641   0.00575   0.00142  -0.0800   0.4940   1.0000
   2.750   0.6909   0.00593   0.00151  -0.0798   0.4747   1.0000
   3.000   0.7177   0.00610   0.00161  -0.0796   0.4569   1.0000
   3.250   0.7446   0.00628   0.00170  -0.0795   0.4370   1.0000
   3.500   0.7710   0.00649   0.00182  -0.0792   0.4157   1.0000
   3.750   0.7976   0.00669   0.00195  -0.0790   0.3946   1.0000
   4.000   0.8240   0.00691   0.00208  -0.0788   0.3748   1.0000
   4.250   0.8504   0.00713   0.00222  -0.0786   0.3570   1.0000
   4.500   0.8767   0.00735   0.00237  -0.0784   0.3375   1.0000
   4.750   0.9029   0.00758   0.00254  -0.0781   0.3185   1.0000
   5.000   0.9290   0.00783   0.00271  -0.0779   0.3015   1.0000
   5.250   0.9549   0.00808   0.00290  -0.0776   0.2836   1.0000
   5.500   0.9808   0.00834   0.00309  -0.0774   0.2653   1.0000
   5.750   1.0060   0.00866   0.00332  -0.0770   0.2448   1.0000
   6.000   1.0314   0.00896   0.00355  -0.0767   0.2254   1.0000
   6.250   1.0567   0.00926   0.00379  -0.0763   0.2087   1.0000
   6.500   1.0814   0.00961   0.00405  -0.0759   0.1903   1.0000
   6.750   1.1062   0.00995   0.00434  -0.0755   0.1734   1.0000
   7.000   1.1309   0.01029   0.00462  -0.0751   0.1578   1.0000
   7.250   1.1548   0.01069   0.00494  -0.0746   0.1393   1.0000
   7.500   1.1782   0.01115   0.00530  -0.0740   0.1213   1.0000
   7.750   1.2019   0.01156   0.00565  -0.0735   0.1068   1.0000
   8.000   1.2251   0.01200   0.00604  -0.0729   0.0918   1.0000
   8.250   1.2479   0.01248   0.00645  -0.0722   0.0779   1.0000
   8.500   1.2705   0.01295   0.00687  -0.0715   0.0662   1.0000
   8.750   1.2923   0.01349   0.00734  -0.0707   0.0537   1.0000
   9.000   1.3137   0.01404   0.00783  -0.0699   0.0432   1.0000
   9.250   1.3349   0.01458   0.00836  -0.0690   0.0352   1.0000
   9.500   1.3554   0.01517   0.00892  -0.0680   0.0282   1.0000
   9.750   1.3764   0.01569   0.00943  -0.0671   0.0236   1.0000
  10.000   1.3957   0.01633   0.01006  -0.0660   0.0176   1.0000
  10.250   1.4112   0.01726   0.01093  -0.0643   0.0092   1.0000
  10.500   1.4271   0.01811   0.01179  -0.0626   0.0062   1.0000
  10.750   1.4436   0.01884   0.01256  -0.0611   0.0053   1.0000
  11.000   1.4565   0.01975   0.01358  -0.0589   0.0045   1.0000
  11.250   1.4692   0.02046   0.01437  -0.0567   0.0043   1.0000
  11.500   1.4801   0.02124   0.01523  -0.0543   0.0041   1.0000
  11.750   1.4902   0.02209   0.01617  -0.0518   0.0039   1.0000
  12.000   1.4993   0.02302   0.01719  -0.0495   0.0038   1.0000
  12.250   1.5074   0.02405   0.01831  -0.0471   0.0037   1.0000
  12.500   1.5145   0.02518   0.01954  -0.0448   0.0036   1.0000
  12.750   1.5205   0.02643   0.02088  -0.0426   0.0035   1.0000
  13.000   1.5248   0.02788   0.02243  -0.0404   0.0034   1.0000
  13.250   1.5277   0.02949   0.02414  -0.0384   0.0033   1.0000
  13.500   1.5286   0.03136   0.02614  -0.0365   0.0033   1.0000
  13.750   1.5292   0.03338   0.02826  -0.0349   0.0032   1.0000
  14.000   1.5263   0.03586   0.03087  -0.0334   0.0032   1.0000
  14.250   1.5221   0.03864   0.03378  -0.0324   0.0031   1.0000
  14.500   1.5142   0.04204   0.03732  -0.0318   0.0030   1.0000
  14.750   1.5058   0.04578   0.04120  -0.0317   0.0030   1.0000
  15.000   1.4995   0.04955   0.04510  -0.0320   0.0030   1.0000
  15.250   1.4831   0.05490   0.05062  -0.0332   0.0029   1.0000
  15.500   1.4706   0.06016   0.05603  -0.0348   0.0029   1.0000
  15.750   1.4566   0.06592   0.06194  -0.0369   0.0029   1.0000
  16.000   1.4444   0.07174   0.06790  -0.0393   0.0029   1.0000
  16.250   1.4267   0.07875   0.07506  -0.0424   0.0029   1.0000
  16.500   1.4029   0.08714   0.08363  -0.0464   0.0028   1.0000
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