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NASA SC(2)-0710 AIRFOIL (sc20710-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0710 AIRFOIL (sc20710-il)
Reynolds number: 100,000
Max Cl/Cd: 33.79 at α=1.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20710-il-100000-n5.txt
Download as CSV file: xf-sc20710-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0710 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.6304   0.09136   0.08552  -0.0406   1.0000   0.0354
 -11.750  -0.6553   0.08075   0.07491  -0.0472   1.0000   0.0351
 -11.500  -0.6843   0.07234   0.06646  -0.0525   1.0000   0.0348
 -11.250  -0.7124   0.06637   0.06040  -0.0549   1.0000   0.0346
 -11.000  -0.7404   0.06206   0.05600  -0.0547   1.0000   0.0344
 -10.750  -0.7652   0.05816   0.05198  -0.0539   1.0000   0.0344
 -10.500  -0.7821   0.05370   0.04725  -0.0545   1.0000   0.0345
 -10.250  -0.7917   0.04911   0.04223  -0.0548   1.0000   0.0350
 -10.000  -0.7926   0.04458   0.03712  -0.0553   1.0000   0.0358
  -9.750  -0.7794   0.04261   0.03509  -0.0551   1.0000   0.0366
  -9.500  -0.7646   0.04060   0.03290  -0.0551   1.0000   0.0376
  -9.250  -0.7482   0.03824   0.03027  -0.0553   1.0000   0.0385
  -9.000  -0.7297   0.03570   0.02739  -0.0555   1.0000   0.0395
  -8.750  -0.7090   0.03331   0.02463  -0.0558   1.0000   0.0408
  -8.500  -0.6868   0.03113   0.02205  -0.0559   1.0000   0.0423
  -8.250  -0.6642   0.02951   0.02023  -0.0559   1.0000   0.0443
  -8.000  -0.6412   0.02848   0.01917  -0.0559   1.0000   0.0465
  -7.750  -0.6172   0.02729   0.01781  -0.0558   1.0000   0.0493
  -7.500  -0.5928   0.02605   0.01632  -0.0555   1.0000   0.0518
  -7.250  -0.5688   0.02496   0.01526  -0.0556   1.0000   0.0549
  -7.000  -0.5438   0.02415   0.01441  -0.0556   1.0000   0.0588
  -6.750  -0.5184   0.02334   0.01343  -0.0554   1.0000   0.0629
  -6.500  -0.4927   0.02245   0.01263  -0.0557   1.0000   0.0675
  -6.250  -0.4663   0.02175   0.01188  -0.0559   1.0000   0.0727
  -6.000  -0.4390   0.02100   0.01116  -0.0564   1.0000   0.0788
  -5.750  -0.4108   0.02040   0.01055  -0.0570   1.0000   0.0860
  -5.500  -0.3814   0.01975   0.00993  -0.0580   1.0000   0.0948
  -5.250  -0.3513   0.01918   0.00940  -0.0590   1.0000   0.1077
  -5.000  -0.3201   0.01861   0.00893  -0.0603   1.0000   0.1262
  -4.750  -0.2875   0.01798   0.00851  -0.0621   1.0000   0.1643
  -4.500  -0.2478   0.01690   0.00807  -0.0661   1.0000   0.2808
  -4.250  -0.2134   0.01604   0.00843  -0.0681   1.0000   0.4999
  -4.000  -0.1952   0.01644   0.00907  -0.0652   1.0000   0.5819
  -3.750  -0.1716   0.01679   0.00939  -0.0640   1.0000   0.6211
  -3.500  -0.1476   0.01715   0.00970  -0.0630   1.0000   0.6490
  -3.250  -0.1278   0.01763   0.01016  -0.0608   1.0000   0.6697
  -3.000  -0.1087   0.01813   0.01063  -0.0585   1.0000   0.6879
  -2.750  -0.0912   0.01866   0.01116  -0.0557   1.0000   0.7052
  -2.500  -0.0746   0.01914   0.01165  -0.0528   1.0000   0.7195
  -2.250  -0.0543   0.01947   0.01196  -0.0510   1.0000   0.7312
  -2.000  -0.0279   0.01968   0.01213  -0.0509   1.0000   0.7422
  -1.750  -0.0090   0.01988   0.01234  -0.0489   1.0000   0.7479
  -1.500   0.0165   0.02003   0.01248  -0.0487   1.0000   0.7548
  -1.250   0.0433   0.02015   0.01259  -0.0490   1.0000   0.7605
  -1.000   0.0765   0.02028   0.01273  -0.0502   0.9960   0.7647
  -0.750   0.1123   0.02041   0.01286  -0.0522   0.9924   0.7693
  -0.500   0.1514   0.02051   0.01297  -0.0552   0.9885   0.7743
  -0.250   0.1881   0.02061   0.01313  -0.0571   0.9840   0.7770
   0.000   0.2241   0.02062   0.01320  -0.0589   0.9763   0.7799
   0.250   0.2663   0.02058   0.01323  -0.0619   0.9680   0.7830
   0.500   0.3138   0.02043   0.01317  -0.0659   0.9585   0.7860
   0.750   0.3628   0.01988   0.01272  -0.0696   0.9380   0.7890
   1.000   0.4162   0.01887   0.01182  -0.0732   0.9104   0.7910
   1.250   0.4561   0.01803   0.01111  -0.0741   0.8805   0.7930
   1.500   0.4863   0.01754   0.01073  -0.0735   0.8429   0.7957
   1.750   0.5586   0.01653   0.00912  -0.0792   0.6403   0.7974
   2.000   0.5796   0.01819   0.00931  -0.0776   0.3670   0.8006
   2.250   0.6028   0.01950   0.00977  -0.0774   0.2127   0.8040
   2.500   0.6268   0.02034   0.01023  -0.0770   0.1476   0.8065
   2.750   0.6505   0.02099   0.01073  -0.0763   0.1189   0.8088
   3.000   0.6752   0.02161   0.01130  -0.0758   0.1032   0.8112
   3.250   0.7004   0.02229   0.01194  -0.0754   0.0924   0.8140
   3.500   0.7262   0.02302   0.01263  -0.0753   0.0834   0.8171
   3.750   0.7540   0.02377   0.01347  -0.0755   0.0767   0.8204
   4.000   0.7768   0.02447   0.01415  -0.0746   0.0710   0.8228
   4.250   0.8011   0.02529   0.01505  -0.0739   0.0661   0.8256
   4.500   0.8266   0.02609   0.01591  -0.0736   0.0614   0.8286
   4.750   0.8526   0.02716   0.01693  -0.0736   0.0573   0.8318
   5.000   0.8813   0.02822   0.01818  -0.0738   0.0535   0.8348
   5.250   0.9061   0.02910   0.01911  -0.0734   0.0500   0.8372
   5.500   0.9306   0.03034   0.02037  -0.0730   0.0474   0.8396
   5.750   0.9569   0.03184   0.02217  -0.0726   0.0453   0.8422
   6.000   0.9826   0.03337   0.02393  -0.0724   0.0431   0.8451
   6.250   1.0076   0.03464   0.02535  -0.0722   0.0410   0.8482
   6.500   1.0307   0.03615   0.02690  -0.0719   0.0393   0.8512
   6.750   1.0506   0.03835   0.02963  -0.0705   0.0378   0.8541
   7.000   1.0689   0.04092   0.03266  -0.0690   0.0368   0.8571
   7.250   1.0853   0.04372   0.03591  -0.0675   0.0359   0.8602
   7.500   1.0994   0.04676   0.03939  -0.0660   0.0352   0.8632
   7.750   1.1094   0.04988   0.04293  -0.0640   0.0346   0.8661
   8.000   1.1178   0.05256   0.04592  -0.0619   0.0340   0.8691
   8.250   1.1270   0.05490   0.04848  -0.0601   0.0334   0.8725
   8.500   1.1354   0.05727   0.05099  -0.0586   0.0327   0.8760
   8.750   1.1288   0.06156   0.05572  -0.0558   0.0323   0.8791
   9.000   1.1102   0.06643   0.06109  -0.0520   0.0320   0.8819
   9.250   1.0865   0.07085   0.06586  -0.0483   0.0319   0.8852
   9.500   1.0622   0.07571   0.07099  -0.0461   0.0319   0.8887
   9.750   1.0362   0.08146   0.07698  -0.0461   0.0319   0.8919
  10.000   1.0102   0.08824   0.08396  -0.0485   0.0321   0.8946
  10.250   0.9851   0.09661   0.09248  -0.0538   0.0323   0.8971
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