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SA7038 (sa7038-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: SA7038 (sa7038-il)
Reynolds number: 200,000
Max Cl/Cd: 72.63 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7038-il-200000-n5.txt
Download as CSV file: xf-sa7038-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3709   0.08186   0.07854  -0.0363   1.0000   0.0198
  -7.750  -0.3787   0.07992   0.07666  -0.0342   1.0000   0.0190
  -7.500  -0.3949   0.07817   0.07499  -0.0316   1.0000   0.0188
  -7.250  -0.3939   0.07415   0.07102  -0.0348   0.9967   0.0180
  -7.000  -0.3749   0.06655   0.06338  -0.0462   0.9889   0.0171
  -6.750  -0.3505   0.05736   0.05407  -0.0595   0.9823   0.0166
  -6.500  -0.3279   0.04993   0.04644  -0.0681   0.9748   0.0169
  -6.250  -0.2996   0.04231   0.03845  -0.0759   0.9704   0.0173
  -6.000  -0.2801   0.03365   0.02910  -0.0802   0.9621   0.0160
  -5.750  -0.2511   0.02718   0.02166  -0.0831   0.9578   0.0150
  -5.500  -0.2245   0.02455   0.01855  -0.0838   0.9522   0.0148
  -5.250  -0.1957   0.02235   0.01595  -0.0845   0.9472   0.0148
  -5.000  -0.1640   0.02038   0.01361  -0.0857   0.9437   0.0149
  -4.750  -0.1372   0.01884   0.01183  -0.0857   0.9375   0.0151
  -4.500  -0.1078   0.01754   0.01033  -0.0860   0.9322   0.0156
  -4.250  -0.0762   0.01645   0.00911  -0.0868   0.9281   0.0160
  -4.000  -0.0509   0.01565   0.00821  -0.0862   0.9201   0.0167
  -3.750  -0.0206   0.01490   0.00738  -0.0866   0.9151   0.0177
  -3.500   0.0056   0.01441   0.00680  -0.0861   0.9072   0.0197
  -3.250   0.0347   0.01378   0.00608  -0.0862   0.9012   0.0207
  -3.000   0.0609   0.01318   0.00539  -0.0858   0.8928   0.0221
  -2.750   0.0901   0.01271   0.00484  -0.0858   0.8862   0.0243
  -2.500   0.1166   0.01236   0.00440  -0.0853   0.8764   0.0287
  -2.250   0.1441   0.01183   0.00397  -0.0850   0.8678   0.0584
  -2.000   0.1711   0.01125   0.00369  -0.0849   0.8588   0.1399
  -1.750   0.1966   0.01060   0.00354  -0.0848   0.8482   0.2734
  -1.500   0.2217   0.00994   0.00343  -0.0844   0.8379   0.4366
  -1.250   0.2466   0.00947   0.00334  -0.0836   0.8275   0.5613
  -1.000   0.2706   0.00911   0.00327  -0.0824   0.8160   0.6661
  -0.750   0.2929   0.00882   0.00321  -0.0805   0.8032   0.7628
  -0.500   0.3160   0.00859   0.00312  -0.0787   0.7898   0.8554
  -0.250   0.3544   0.00843   0.00293  -0.0802   0.7757   0.9534
   0.000   0.3911   0.00840   0.00276  -0.0819   0.7603   1.0000
   0.250   0.4174   0.00847   0.00266  -0.0814   0.7445   1.0000
   0.500   0.4436   0.00854   0.00260  -0.0809   0.7275   1.0000
   0.750   0.4699   0.00864   0.00256  -0.0804   0.7100   1.0000
   1.000   0.4961   0.00875   0.00253  -0.0799   0.6918   1.0000
   1.250   0.5222   0.00888   0.00252  -0.0795   0.6732   1.0000
   1.500   0.5483   0.00903   0.00254  -0.0790   0.6536   1.0000
   1.750   0.5742   0.00919   0.00257  -0.0785   0.6341   1.0000
   2.000   0.6001   0.00936   0.00264  -0.0780   0.6147   1.0000
   2.250   0.6259   0.00954   0.00271  -0.0776   0.5949   1.0000
   2.500   0.6516   0.00975   0.00280  -0.0771   0.5753   1.0000
   2.750   0.6772   0.00995   0.00291  -0.0766   0.5557   1.0000
   3.000   0.7027   0.01017   0.00305  -0.0761   0.5355   1.0000
   3.250   0.7280   0.01041   0.00319  -0.0756   0.5153   1.0000
   3.500   0.7533   0.01065   0.00335  -0.0751   0.4945   1.0000
   3.750   0.7782   0.01092   0.00353  -0.0746   0.4742   1.0000
   4.000   0.8033   0.01118   0.00375  -0.0741   0.4534   1.0000
   4.250   0.8281   0.01147   0.00396  -0.0736   0.4335   1.0000
   4.500   0.8529   0.01176   0.00419  -0.0730   0.4136   1.0000
   4.750   0.8774   0.01208   0.00444  -0.0725   0.3935   1.0000
   5.000   0.9016   0.01242   0.00474  -0.0719   0.3729   1.0000
   5.250   0.9257   0.01276   0.00504  -0.0713   0.3518   1.0000
   5.500   0.9495   0.01314   0.00535  -0.0707   0.3318   1.0000
   5.750   0.9734   0.01351   0.00569  -0.0701   0.3123   1.0000
   6.000   0.9969   0.01391   0.00607  -0.0695   0.2934   1.0000
   6.250   1.0200   0.01433   0.00646  -0.0688   0.2754   1.0000
   6.500   1.0434   0.01475   0.00687  -0.0682   0.2579   1.0000
   6.750   1.0662   0.01520   0.00730  -0.0675   0.2400   1.0000
   7.000   1.0885   0.01569   0.00777  -0.0667   0.2224   1.0000
   7.250   1.1103   0.01621   0.00828  -0.0659   0.2041   1.0000
   7.500   1.1319   0.01675   0.00880  -0.0651   0.1857   1.0000
   7.750   1.1531   0.01732   0.00936  -0.0642   0.1691   1.0000
   8.000   1.1737   0.01792   0.00994  -0.0633   0.1534   1.0000
   8.500   1.2135   0.01921   0.01125  -0.0613   0.1241   1.0000
   8.750   1.2326   0.01989   0.01195  -0.0601   0.1106   1.0000
   9.000   1.2509   0.02062   0.01269  -0.0589   0.0982   1.0000
   9.250   1.2682   0.02141   0.01349  -0.0576   0.0856   1.0000
   9.500   1.2844   0.02226   0.01433  -0.0562   0.0729   1.0000
   9.750   1.2993   0.02317   0.01524  -0.0546   0.0612   1.0000
  10.000   1.3126   0.02408   0.01616  -0.0528   0.0513   1.0000
  10.250   1.3246   0.02501   0.01716  -0.0508   0.0431   1.0000
  10.500   1.3351   0.02603   0.01822  -0.0487   0.0364   1.0000
  10.750   1.3433   0.02725   0.01943  -0.0465   0.0301   1.0000
  11.000   1.3534   0.02832   0.02063  -0.0445   0.0253   1.0000
  11.250   1.3598   0.02970   0.02206  -0.0424   0.0209   1.0000
  11.500   1.3650   0.03123   0.02365  -0.0404   0.0160   1.0000
  11.750   1.3696   0.03284   0.02539  -0.0384   0.0135   1.0000
  12.000   1.3718   0.03473   0.02738  -0.0365   0.0114   1.0000
  12.250   1.3713   0.03692   0.02968  -0.0347   0.0103   1.0000
  12.500   1.3721   0.03913   0.03208  -0.0333   0.0095   1.0000
  12.750   1.3708   0.04165   0.03478  -0.0322   0.0088   1.0000
  13.000   1.3688   0.04441   0.03773  -0.0315   0.0083   1.0000
  13.250   1.3657   0.04743   0.04092  -0.0311   0.0080   1.0000
  13.500   1.3603   0.05093   0.04457  -0.0311   0.0076   1.0000
  13.750   1.3524   0.05497   0.04878  -0.0316   0.0074   1.0000
  14.000   1.3434   0.05940   0.05338  -0.0326   0.0072   1.0000
  14.250   1.3339   0.06416   0.05832  -0.0340   0.0071   1.0000
  14.500   1.3227   0.06947   0.06379  -0.0359   0.0070   1.0000
  14.750   1.3123   0.07492   0.06942  -0.0381   0.0069   1.0000
  15.000   1.3012   0.08071   0.07539  -0.0406   0.0069   1.0000
  15.250   1.2892   0.08692   0.08178  -0.0435   0.0068   1.0000
  15.500   1.2769   0.09340   0.08843  -0.0466   0.0067   1.0000
  15.750   1.2646   0.10007   0.09526  -0.0500   0.0067   1.0000
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