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ARA-D 10% AIRFOIL (arad10-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: ARA-D 10% AIRFOIL (arad10-il)
Reynolds number: 50,000
Max Cl/Cd: 36.73 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-arad10-il-50000-n5.txt
Download as CSV file: xf-arad10-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ARA-D 10% AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3752   0.11311   0.10586  -0.0216   1.0000   0.1095
  -8.500  -0.3740   0.10991   0.10273  -0.0227   1.0000   0.1096
  -8.250  -0.3755   0.10202   0.09481  -0.0260   1.0000   0.0727
  -8.000  -0.3699   0.09870   0.09154  -0.0257   1.0000   0.0714
  -7.750  -0.3694   0.09541   0.08834  -0.0264   1.0000   0.0704
  -7.500  -0.3685   0.09192   0.08492  -0.0278   1.0000   0.0695
  -7.250  -0.3677   0.08829   0.08136  -0.0296   1.0000   0.0686
  -7.000  -0.3667   0.08444   0.07756  -0.0316   1.0000   0.0676
  -6.500  -0.3621   0.07350   0.06654  -0.0406   1.0000   0.0635
  -6.250  -0.3539   0.06967   0.06269  -0.0418   1.0000   0.0632
  -6.000  -0.3440   0.06551   0.05846  -0.0435   1.0000   0.0630
  -5.750  -0.3312   0.06062   0.05340  -0.0462   1.0000   0.0632
  -5.500  -0.3165   0.05632   0.04894  -0.0482   1.0000   0.0645
  -5.250  -0.3029   0.05457   0.04719  -0.0475   1.0000   0.0665
  -5.000  -0.2852   0.05099   0.04340  -0.0489   1.0000   0.0683
  -4.750  -0.2642   0.04675   0.03879  -0.0509   1.0000   0.0698
  -4.500  -0.2370   0.04117   0.03239  -0.0542   1.0000   0.0735
  -4.250  -0.2202   0.04041   0.03173  -0.0532   1.0000   0.0762
  -4.000  -0.1980   0.03827   0.02927  -0.0536   1.0000   0.0800
  -3.750  -0.1720   0.03557   0.02597  -0.0545   1.0000   0.0855
  -3.500  -0.1443   0.03453   0.02486  -0.0555   0.9974   0.0907
  -3.250  -0.1020   0.03247   0.02228  -0.0589   0.9912   0.0991
  -3.000  -0.0604   0.03117   0.02064  -0.0620   0.9844   0.1088
  -2.750  -0.0211   0.03015   0.01950  -0.0646   0.9764   0.1182
  -2.500   0.0214   0.02908   0.01815  -0.0677   0.9696   0.1295
  -2.250   0.0602   0.02827   0.01706  -0.0698   0.9604   0.1421
  -2.000   0.0995   0.02759   0.01635  -0.0722   0.9521   0.1554
  -1.750   0.1396   0.02698   0.01565  -0.0745   0.9433   0.1711
  -1.500   0.1782   0.02647   0.01506  -0.0766   0.9336   0.1892
  -1.250   0.2211   0.02591   0.01445  -0.0793   0.9256   0.2112
  -1.000   0.2576   0.02542   0.01403  -0.0810   0.9146   0.2346
  -0.750   0.2991   0.02481   0.01352  -0.0835   0.9061   0.2665
  -0.500   0.3340   0.02425   0.01317  -0.0847   0.8939   0.3089
  -0.250   0.3671   0.02326   0.01293  -0.0858   0.8819   0.4282
   0.000   0.3968   0.02177   0.01252  -0.0846   0.8680   1.0000
   0.250   0.4324   0.02171   0.01216  -0.0853   0.8533   1.0000
   0.500   0.4656   0.02161   0.01183  -0.0854   0.8360   1.0000
   0.750   0.4969   0.02150   0.01153  -0.0851   0.8172   1.0000
   1.000   0.5271   0.02141   0.01127  -0.0846   0.7978   1.0000
   1.250   0.5566   0.02135   0.01106  -0.0839   0.7785   1.0000
   1.500   0.5855   0.02131   0.01087  -0.0832   0.7590   1.0000
   1.750   0.6141   0.02128   0.01070  -0.0824   0.7392   1.0000
   2.000   0.6400   0.02138   0.01070  -0.0813   0.7164   1.0000
   2.250   0.6667   0.02146   0.01065  -0.0802   0.6936   1.0000
   2.500   0.6936   0.02153   0.01059  -0.0792   0.6704   1.0000
   2.750   0.7191   0.02171   0.01066  -0.0781   0.6442   1.0000
   3.000   0.7450   0.02188   0.01069  -0.0771   0.6180   1.0000
   3.250   0.7702   0.02212   0.01081  -0.0760   0.5896   1.0000
   3.500   0.7948   0.02241   0.01097  -0.0749   0.5592   1.0000
   3.750   0.8192   0.02275   0.01116  -0.0738   0.5280   1.0000
   4.000   0.8431   0.02316   0.01140  -0.0727   0.4957   1.0000
   4.250   0.8666   0.02366   0.01171  -0.0716   0.4635   1.0000
   4.500   0.8899   0.02423   0.01209  -0.0706   0.4333   1.0000
   4.750   0.9129   0.02488   0.01254  -0.0696   0.4053   1.0000
   5.000   0.9359   0.02558   0.01311  -0.0688   0.3802   1.0000
   5.250   0.9591   0.02632   0.01371  -0.0680   0.3589   1.0000
   5.500   0.9823   0.02710   0.01435  -0.0672   0.3403   1.0000
   5.750   1.0056   0.02790   0.01506  -0.0666   0.3239   1.0000
   6.000   1.0293   0.02873   0.01583  -0.0660   0.3093   1.0000
   6.250   1.0528   0.02958   0.01664  -0.0654   0.2963   1.0000
   6.500   1.0764   0.03046   0.01746  -0.0648   0.2847   1.0000
   6.750   1.1001   0.03136   0.01833  -0.0642   0.2742   1.0000
   7.000   1.1234   0.03230   0.01934  -0.0637   0.2639   1.0000
   7.250   1.1471   0.03325   0.02020  -0.0631   0.2552   1.0000
   7.500   1.1696   0.03427   0.02139  -0.0625   0.2460   1.0000
   7.750   1.1931   0.03528   0.02235  -0.0620   0.2386   1.0000
   8.000   1.2143   0.03639   0.02364  -0.0612   0.2303   1.0000
   8.250   1.2380   0.03743   0.02459  -0.0608   0.2238   1.0000
   8.500   1.2573   0.03873   0.02619  -0.0599   0.2164   1.0000
   8.750   1.2790   0.03984   0.02731  -0.0592   0.2102   1.0000
   9.000   1.2981   0.04123   0.02890  -0.0583   0.2040   1.0000
   9.250   1.3165   0.04262   0.03047  -0.0573   0.1980   1.0000
   9.500   1.3389   0.04376   0.03154  -0.0568   0.1930   1.0000
   9.750   1.3511   0.04559   0.03375  -0.0552   0.1872   1.0000
  10.000   1.3665   0.04712   0.03547  -0.0540   0.1820   1.0000
  10.250   1.3879   0.04834   0.03664  -0.0534   0.1778   1.0000
  10.500   1.3932   0.05064   0.03937  -0.0512   0.1731   1.0000
  10.750   1.4011   0.05265   0.04163  -0.0494   0.1685   1.0000
  11.000   1.4161   0.05409   0.04315  -0.0482   0.1645   1.0000
  11.250   1.4254   0.05613   0.04534  -0.0466   0.1611   1.0000
  11.500   1.4150   0.05927   0.04891  -0.0434   0.1578   1.0000
  11.750   1.4053   0.06210   0.05202  -0.0403   0.1548   1.0000
  12.000   1.4020   0.06451   0.05460  -0.0380   0.1519   1.0000
  12.250   1.4181   0.06578   0.05584  -0.0370   0.1487   1.0000
  12.500   1.3968   0.06987   0.06021  -0.0345   0.1470   1.0000
  12.750   1.3539   0.07645   0.06717  -0.0330   0.1458   1.0000
  13.000   1.2891   0.08715   0.07824  -0.0352   0.1453   1.0000
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