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ARA-D 20% AIRFOIL (arad20-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: ARA-D 20% AIRFOIL (arad20-il)
Reynolds number: 100,000
Max Cl/Cd: 24.85 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-arad20-il-100000.txt
Download as CSV file: xf-arad20-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ARA-D 20% AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.6204   0.08316   0.07801  -0.0337   1.0000   0.0844
 -11.500  -0.6560   0.07447   0.06920  -0.0387   1.0000   0.0833
 -11.250  -0.7071   0.06663   0.06111  -0.0412   1.0000   0.0819
 -11.000  -0.7558   0.06062   0.05473  -0.0393   1.0000   0.0808
 -10.750  -0.7785   0.05552   0.04923  -0.0376   1.0000   0.0807
 -10.500  -0.7836   0.05161   0.04496  -0.0362   1.0000   0.0816
 -10.250  -0.7843   0.04786   0.04075  -0.0348   1.0000   0.0832
 -10.000  -0.7826   0.04413   0.03635  -0.0333   1.0000   0.0851
  -9.750  -0.7556   0.04284   0.03537  -0.0334   1.0000   0.0876
  -9.500  -0.7378   0.04062   0.03295  -0.0328   1.0000   0.0902
  -9.250  -0.7224   0.03800   0.02981  -0.0321   1.0000   0.0932
  -9.000  -0.6959   0.03677   0.02890  -0.0324   1.0000   0.0965
  -8.750  -0.6751   0.03509   0.02703  -0.0324   1.0000   0.1005
  -8.500  -0.6192   0.03323   0.02513  -0.0384   0.9115   0.1067
  -8.250  -0.5943   0.03203   0.02342  -0.0373   0.8423   0.1119
  -8.000  -0.5723   0.03134   0.02260  -0.0357   0.7984   0.1167
  -7.750  -0.5486   0.03035   0.02128  -0.0346   0.7693   0.1226
  -7.500  -0.5231   0.02962   0.02046  -0.0340   0.7467   0.1289
  -7.250  -0.4971   0.02872   0.01945  -0.0334   0.7279   0.1360
  -7.000  -0.4700   0.02806   0.01854  -0.0331   0.7114   0.1448
  -6.750  -0.4434   0.02730   0.01787  -0.0328   0.6981   0.1538
  -6.500  -0.4159   0.02654   0.01713  -0.0326   0.6851   0.1645
  -6.250  -0.3887   0.02590   0.01646  -0.0324   0.6742   0.1775
  -6.000  -0.3609   0.02526   0.01587  -0.0324   0.6629   0.1932
  -5.750  -0.3340   0.02475   0.01535  -0.0320   0.6540   0.2119
  -5.500  -0.3053   0.02419   0.01490  -0.0323   0.6439   0.2360
  -5.250  -0.2782   0.02365   0.01451  -0.0321   0.6352   0.2634
  -5.000  -0.2503   0.02325   0.01424  -0.0321   0.6271   0.2983
  -4.750  -0.2221   0.02285   0.01408  -0.0323   0.6182   0.3390
  -4.500  -0.1947   0.02259   0.01398  -0.0320   0.6108   0.3834
  -4.250  -0.1667   0.02247   0.01406  -0.0319   0.6033   0.4298
  -4.000  -0.1383   0.02238   0.01418  -0.0318   0.5950   0.4755
  -3.750  -0.1107   0.02242   0.01431  -0.0313   0.5880   0.5185
  -3.500  -0.0829   0.02261   0.01457  -0.0308   0.5815   0.5587
  -3.250  -0.0546   0.02275   0.01485  -0.0304   0.5735   0.5964
  -3.000  -0.0278   0.02293   0.01510  -0.0294   0.5665   0.6294
  -2.750  -0.0016   0.02329   0.01540  -0.0283   0.5608   0.6612
  -2.500   0.0260   0.02355   0.01577  -0.0277   0.5533   0.6922
  -2.250   0.0513   0.02380   0.01610  -0.0263   0.5463   0.7190
  -2.000   0.0757   0.02409   0.01634  -0.0246   0.5405   0.7449
  -1.750   0.0997   0.02449   0.01675  -0.0230   0.5346   0.7698
  -1.500   0.1234   0.02478   0.01712  -0.0214   0.5273   0.7940
  -1.250   0.1459   0.02499   0.01730  -0.0193   0.5211   0.8176
  -1.000   0.1676   0.02523   0.01743  -0.0170   0.5161   0.8408
  -0.750   0.1895   0.02557   0.01783  -0.0152   0.5098   0.8638
  -0.500   0.2122   0.02577   0.01804  -0.0134   0.5028   0.8871
  -0.250   0.2371   0.02585   0.01803  -0.0120   0.4971   0.9109
   0.000   0.2685   0.02609   0.01809  -0.0118   0.4922   0.9323
   0.250   0.3097   0.02661   0.01873  -0.0146   0.4836   0.9503
   0.500   0.3596   0.02693   0.01893  -0.0188   0.4762   0.9651
   0.750   0.4168   0.02733   0.01907  -0.0242   0.4704   0.9752
   1.000   0.4721   0.02815   0.02002  -0.0305   0.4609   0.9851
   1.250   0.5267   0.02839   0.02013  -0.0360   0.4539   0.9954
   1.500   0.5586   0.02845   0.01999  -0.0375   0.4495   1.0000
   1.750   0.5681   0.02901   0.02065  -0.0361   0.4438   1.0000
   2.000   0.5779   0.02940   0.02106  -0.0343   0.4380   1.0000
   2.250   0.5915   0.02950   0.02106  -0.0325   0.4335   1.0000
   2.500   0.6120   0.02957   0.02096  -0.0315   0.4298   1.0000
   2.750   0.6342   0.03047   0.02188  -0.0316   0.4242   1.0000
   3.000   0.6579   0.03143   0.02291  -0.0320   0.4173   1.0000
   3.250   0.6865   0.03166   0.02302  -0.0324   0.4127   1.0000
   3.500   0.7170   0.03174   0.02290  -0.0327   0.4091   1.0000
   3.750   0.7385   0.03328   0.02461  -0.0332   0.4022   1.0000
   4.000   0.7634   0.03421   0.02557  -0.0336   0.3963   1.0000
   4.250   0.7933   0.03432   0.02556  -0.0339   0.3923   1.0000
   4.500   0.8252   0.03429   0.02533  -0.0342   0.3892   1.0000
   4.750   0.8387   0.03673   0.02807  -0.0343   0.3814   1.0000
   5.000   0.8631   0.03758   0.02892  -0.0344   0.3764   1.0000
   5.250   0.8941   0.03753   0.02876  -0.0347   0.3730   1.0000
   5.500   0.9275   0.03733   0.02836  -0.0350   0.3703   1.0000
   5.750   0.9256   0.04129   0.03276  -0.0343   0.3618   1.0000
   6.000   0.9492   0.04207   0.03353  -0.0343   0.3575   1.0000
   6.250   0.9825   0.04174   0.03308  -0.0345   0.3546   1.0000
   6.500   1.0188   0.04123   0.03237  -0.0350   0.3522   1.0000
   6.750   0.9576   0.05084   0.04271  -0.0318   0.3413   1.0000
   7.000   0.9937   0.05010   0.04187  -0.0319   0.3386   1.0000
   7.250   1.0403   0.04842   0.04003  -0.0325   0.3367   1.0000
   7.500   1.0853   0.04706   0.03847  -0.0333   0.3348   1.0000
   7.750   0.6404   0.10814   0.10069  -0.0435   0.3143   1.0000
   8.000   0.6357   0.11368   0.10626  -0.0451   0.3149   1.0000
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