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NASA SC(2)-0410 AIRFOIL (sc20410-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0410 AIRFOIL (sc20410-il)
Reynolds number: 500,000
Max Cl/Cd: 53.96 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20410-il-500000.txt
Download as CSV file: xf-sc20410-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0410 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.9053   0.06052   0.05751  -0.0398   1.0000   0.0215
 -12.000  -0.9528   0.05127   0.04791  -0.0439   1.0000   0.0212
 -11.750  -0.9904   0.04453   0.04079  -0.0446   1.0000   0.0210
 -11.500  -1.0113   0.03987   0.03579  -0.0440   1.0000   0.0209
 -11.250  -1.0141   0.03607   0.03164  -0.0439   1.0000   0.0210
 -11.000  -1.0079   0.03315   0.02842  -0.0434   1.0000   0.0212
 -10.750  -0.9964   0.03071   0.02571  -0.0429   1.0000   0.0214
 -10.500  -0.9816   0.02860   0.02336  -0.0424   1.0000   0.0217
 -10.250  -0.9643   0.02678   0.02131  -0.0420   1.0000   0.0220
 -10.000  -0.9452   0.02519   0.01952  -0.0415   1.0000   0.0223
  -9.750  -0.9248   0.02382   0.01798  -0.0411   1.0000   0.0227
  -9.500  -0.9031   0.02272   0.01672  -0.0407   1.0000   0.0231
  -9.250  -0.8824   0.02119   0.01503  -0.0402   1.0000   0.0237
  -9.000  -0.8606   0.02003   0.01384  -0.0399   1.0000   0.0244
  -8.750  -0.8372   0.01930   0.01308  -0.0396   1.0000   0.0251
  -8.500  -0.8135   0.01855   0.01228  -0.0394   1.0000   0.0258
  -8.250  -0.7894   0.01781   0.01148  -0.0391   1.0000   0.0266
  -8.000  -0.7651   0.01712   0.01071  -0.0388   1.0000   0.0275
  -7.750  -0.7401   0.01659   0.01010  -0.0386   1.0000   0.0283
  -7.500  -0.7160   0.01545   0.00897  -0.0387   1.0000   0.0300
  -7.250  -0.6905   0.01498   0.00850  -0.0386   1.0000   0.0317
  -7.000  -0.6648   0.01456   0.00803  -0.0385   1.0000   0.0338
  -6.750  -0.6387   0.01384   0.00734  -0.0387   1.0000   0.0367
  -6.500  -0.6128   0.01356   0.00706  -0.0386   1.0000   0.0399
  -6.250  -0.5862   0.01304   0.00652  -0.0388   1.0000   0.0434
  -6.000  -0.5599   0.01271   0.00622  -0.0388   1.0000   0.0468
  -5.750  -0.5339   0.01249   0.00598  -0.0386   1.0000   0.0498
  -5.500  -0.5062   0.01195   0.00545  -0.0391   1.0000   0.0539
  -5.250  -0.4796   0.01170   0.00521  -0.0392   1.0000   0.0578
  -5.000  -0.4531   0.01150   0.00499  -0.0391   1.0000   0.0612
  -4.750  -0.4250   0.01110   0.00464  -0.0396   1.0000   0.0679
  -4.500  -0.3982   0.01091   0.00445  -0.0397   1.0000   0.0737
  -4.250  -0.3697   0.01058   0.00419  -0.0403   1.0000   0.0835
  -4.000  -0.3407   0.01027   0.00394  -0.0409   1.0000   0.0973
  -3.750  -0.3095   0.00985   0.00372  -0.0421   1.0000   0.1333
  -3.500  -0.2717   0.00900   0.00342  -0.0453   1.0000   0.2544
  -3.250  -0.2244   0.00768   0.00298  -0.0509   1.0000   0.4673
  -3.000  -0.1891   0.00731   0.00313  -0.0528   1.0000   0.6080
  -2.750  -0.1617   0.00743   0.00329  -0.0528   1.0000   0.6362
  -2.500  -0.1326   0.00757   0.00342  -0.0531   0.9994   0.6551
  -2.250  -0.0954   0.00762   0.00348  -0.0550   0.9965   0.6697
  -2.000  -0.0572   0.00768   0.00357  -0.0570   0.9941   0.6811
  -1.750  -0.0202   0.00767   0.00354  -0.0589   0.9894   0.6901
  -1.500   0.0189   0.00770   0.00362  -0.0610   0.9857   0.6998
  -1.250   0.0586   0.00773   0.00369  -0.0631   0.9816   0.7106
  -1.000   0.0987   0.00771   0.00369  -0.0653   0.9756   0.7190
  -0.750   0.1411   0.00757   0.00357  -0.0681   0.9709   0.7239
  -0.500   0.1740   0.00751   0.00357  -0.0687   0.9605   0.7281
  -0.250   0.2067   0.00749   0.00355  -0.0692   0.9466   0.7332
   0.000   0.2378   0.00747   0.00350  -0.0695   0.9282   0.7378
   0.250   0.2652   0.00745   0.00346  -0.0689   0.9064   0.7407
   0.500   0.2920   0.00747   0.00345  -0.0682   0.8832   0.7429
   0.750   0.3189   0.00752   0.00344  -0.0676   0.8538   0.7449
   1.000   0.3456   0.00762   0.00342  -0.0669   0.8179   0.7471
   1.250   0.3725   0.00777   0.00342  -0.0664   0.7718   0.7494
   1.500   0.3988   0.00804   0.00342  -0.0658   0.7014   0.7515
   1.750   0.4225   0.00877   0.00348  -0.0649   0.5468   0.7534
   2.000   0.4463   0.00981   0.00372  -0.0646   0.3666   0.7551
   2.250   0.4715   0.01052   0.00393  -0.0644   0.2450   0.7568
   2.500   0.4974   0.01112   0.00417  -0.0642   0.1603   0.7584
   2.750   0.5242   0.01158   0.00441  -0.0641   0.1135   0.7601
   3.000   0.5516   0.01194   0.00466  -0.0641   0.0907   0.7619
   3.250   0.5791   0.01230   0.00496  -0.0640   0.0786   0.7639
   3.500   0.6072   0.01257   0.00519  -0.0641   0.0706   0.7660
   3.750   0.6352   0.01288   0.00549  -0.0641   0.0645   0.7681
   4.000   0.6634   0.01316   0.00575  -0.0642   0.0598   0.7701
   4.250   0.6906   0.01361   0.00620  -0.0642   0.0551   0.7719
   4.500   0.7182   0.01380   0.00643  -0.0641   0.0516   0.7736
   4.750   0.7449   0.01416   0.00677  -0.0639   0.0476   0.7754
   5.000   0.7716   0.01454   0.00721  -0.0636   0.0443   0.7773
   5.250   0.7990   0.01482   0.00749  -0.0635   0.0409   0.7795
   5.500   0.8248   0.01544   0.00812  -0.0632   0.0375   0.7821
   5.750   0.8521   0.01579   0.00850  -0.0631   0.0347   0.7846
   6.000   0.8783   0.01639   0.00906  -0.0629   0.0323   0.7869
   6.250   0.9033   0.01705   0.00981  -0.0623   0.0306   0.7888
   6.500   0.9293   0.01749   0.01032  -0.0620   0.0290   0.7909
   6.750   0.9551   0.01794   0.01080  -0.0616   0.0276   0.7932
   7.000   0.9796   0.01875   0.01163  -0.0611   0.0266   0.7958
   7.250   1.0034   0.01987   0.01285  -0.0605   0.0257   0.7984
   7.500   1.0288   0.02062   0.01371  -0.0601   0.0251   0.8012
   7.750   1.0532   0.02147   0.01467  -0.0594   0.0245   0.8035
   8.000   1.0769   0.02238   0.01571  -0.0587   0.0239   0.8058
   8.250   1.1004   0.02333   0.01680  -0.0581   0.0233   0.8085
   8.500   1.1236   0.02431   0.01789  -0.0574   0.0229   0.8115
   8.750   1.1465   0.02535   0.01903  -0.0568   0.0224   0.8146
   9.000   1.1683   0.02656   0.02033  -0.0560   0.0220   0.8176
   9.250   1.1853   0.02891   0.02289  -0.0547   0.0215   0.8203
   9.500   1.2025   0.03079   0.02507  -0.0533   0.0212   0.8235
   9.750   1.2192   0.03259   0.02718  -0.0518   0.0209   0.8270
  10.000   1.2322   0.03505   0.02997  -0.0501   0.0207   0.8305
  10.250   1.2395   0.03810   0.03342  -0.0478   0.0205   0.8335
  10.500   1.2392   0.04196   0.03772  -0.0449   0.0204   0.8367
  10.750   1.2278   0.04681   0.04305  -0.0413   0.0204   0.8403
  11.000   1.2038   0.05230   0.04898  -0.0372   0.0205   0.8443
  11.250   1.1721   0.05686   0.05382  -0.0327   0.0205   0.8485
  11.500   1.1395   0.06239   0.05963  -0.0311   0.0207   0.8524
  11.750   1.1054   0.06961   0.06709  -0.0335   0.0208   0.8565
  12.000   1.0678   0.08055   0.07825  -0.0419   0.0210   0.8601
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