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NASA SC(2)-0010 AIRFOIL (sc20010-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0010 AIRFOIL (sc20010-il)
Reynolds number: 100,000
Max Cl/Cd: 28.66 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20010-il-100000-n5.txt
Download as CSV file: xf-sc20010-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0010 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.7733   0.09151   0.08604  -0.0078   1.0000   0.0339
 -11.250  -0.7989   0.08087   0.07533  -0.0159   1.0000   0.0336
 -11.000  -0.8260   0.07280   0.06713  -0.0214   1.0000   0.0334
 -10.750  -0.8518   0.06665   0.06079  -0.0240   1.0000   0.0332
 -10.500  -0.8757   0.06177   0.05570  -0.0239   1.0000   0.0332
 -10.250  -0.8955   0.05736   0.05100  -0.0222   1.0000   0.0332
 -10.000  -0.9085   0.05274   0.04598  -0.0204   1.0000   0.0334
  -9.750  -0.9151   0.04829   0.04103  -0.0186   1.0000   0.0336
  -9.500  -0.9132   0.04459   0.03688  -0.0169   1.0000   0.0341
  -9.250  -0.8992   0.04284   0.03504  -0.0160   1.0000   0.0349
  -9.000  -0.8845   0.04111   0.03315  -0.0151   1.0000   0.0360
  -8.750  -0.8699   0.03900   0.03077  -0.0141   1.0000   0.0373
  -8.500  -0.8550   0.03646   0.02783  -0.0129   1.0000   0.0386
  -8.250  -0.8380   0.03386   0.02478  -0.0117   1.0000   0.0398
  -8.000  -0.8184   0.03159   0.02211  -0.0107   1.0000   0.0411
  -7.750  -0.7971   0.03010   0.02057  -0.0101   1.0000   0.0424
  -7.500  -0.7751   0.02889   0.01926  -0.0095   1.0000   0.0445
  -7.250  -0.7525   0.02760   0.01774  -0.0089   1.0000   0.0476
  -7.000  -0.7296   0.02623   0.01623  -0.0082   1.0000   0.0503
  -6.750  -0.7067   0.02515   0.01515  -0.0077   1.0000   0.0531
  -6.500  -0.6832   0.02418   0.01403  -0.0070   1.0000   0.0573
  -6.250  -0.6604   0.02313   0.01296  -0.0064   1.0000   0.0614
  -6.000  -0.6374   0.02231   0.01213  -0.0057   1.0000   0.0663
  -5.750  -0.6144   0.02144   0.01119  -0.0049   1.0000   0.0717
  -5.500  -0.5921   0.02068   0.01049  -0.0042   1.0000   0.0775
  -5.250  -0.5695   0.01997   0.00972  -0.0033   1.0000   0.0839
  -5.000  -0.5480   0.01927   0.00907  -0.0024   1.0000   0.0908
  -4.750  -0.5264   0.01863   0.00845  -0.0014   1.0000   0.0987
  -4.500  -0.5052   0.01805   0.00790  -0.0004   1.0000   0.1083
  -4.250  -0.4849   0.01746   0.00739   0.0008   1.0000   0.1203
  -4.000  -0.4650   0.01690   0.00691   0.0020   1.0000   0.1365
  -3.750  -0.4457   0.01632   0.00652   0.0033   1.0000   0.1631
  -3.500  -0.4275   0.01570   0.00617   0.0046   1.0000   0.2114
  -3.250  -0.4107   0.01489   0.00586   0.0060   1.0000   0.2995
  -3.000  -0.3934   0.01377   0.00561   0.0073   0.9984   0.4687
  -2.750  -0.3656   0.01333   0.00595   0.0079   0.9919   0.6520
  -2.500  -0.3331   0.01334   0.00602   0.0072   0.9850   0.7129
  -2.250  -0.3017   0.01339   0.00607   0.0068   0.9781   0.7546
  -2.000  -0.2698   0.01348   0.00621   0.0067   0.9723   0.7902
  -1.750  -0.2392   0.01360   0.00635   0.0068   0.9658   0.8204
  -1.500  -0.2082   0.01377   0.00655   0.0071   0.9594   0.8484
  -1.250  -0.1760   0.01394   0.00671   0.0071   0.9540   0.8738
  -1.000  -0.1442   0.01405   0.00680   0.0067   0.9472   0.8907
  -0.750  -0.1069   0.01412   0.00683   0.0050   0.9421   0.9015
  -0.500  -0.0712   0.01412   0.00681   0.0034   0.9359   0.9095
  -0.250  -0.0357   0.01414   0.00681   0.0018   0.9294   0.9168
   0.000   0.0000   0.01413   0.00679   0.0000   0.9241   0.9241
   0.250   0.0357   0.01414   0.00681  -0.0018   0.9168   0.9294
   0.500   0.0712   0.01412   0.00681  -0.0034   0.9095   0.9359
   0.750   0.1069   0.01412   0.00683  -0.0050   0.9015   0.9421
   1.000   0.1442   0.01405   0.00680  -0.0067   0.8907   0.9472
   1.250   0.1760   0.01394   0.00671  -0.0071   0.8738   0.9540
   1.500   0.2083   0.01377   0.00655  -0.0071   0.8485   0.9594
   1.750   0.2392   0.01360   0.00635  -0.0068   0.8205   0.9658
   2.000   0.2698   0.01348   0.00621  -0.0067   0.7902   0.9723
   2.250   0.3017   0.01339   0.00607  -0.0068   0.7545   0.9782
   2.500   0.3331   0.01334   0.00601  -0.0072   0.7129   0.9851
   2.750   0.3657   0.01333   0.00595  -0.0079   0.6520   0.9919
   3.000   0.3934   0.01377   0.00561  -0.0073   0.4686   0.9985
   3.250   0.4107   0.01489   0.00585  -0.0060   0.2996   1.0000
   3.500   0.4274   0.01569   0.00617  -0.0046   0.2115   1.0000
   3.750   0.4457   0.01632   0.00652  -0.0033   0.1631   1.0000
   4.000   0.4649   0.01690   0.00691  -0.0020   0.1365   1.0000
   4.250   0.4849   0.01746   0.00739  -0.0008   0.1203   1.0000
   4.500   0.5052   0.01805   0.00789   0.0004   0.1083   1.0000
   4.750   0.5263   0.01863   0.00845   0.0014   0.0987   1.0000
   5.000   0.5479   0.01926   0.00907   0.0024   0.0908   1.0000
   5.250   0.5695   0.01997   0.00972   0.0033   0.0839   1.0000
   5.500   0.5921   0.02068   0.01048   0.0042   0.0775   1.0000
   5.750   0.6144   0.02144   0.01119   0.0049   0.0717   1.0000
   6.000   0.6374   0.02231   0.01213   0.0057   0.0663   1.0000
   6.250   0.6604   0.02313   0.01297   0.0064   0.0614   1.0000
   6.500   0.6833   0.02418   0.01403   0.0070   0.0573   1.0000
   6.750   0.7068   0.02515   0.01515   0.0076   0.0531   1.0000
   7.000   0.7296   0.02623   0.01623   0.0082   0.0503   1.0000
   7.250   0.7525   0.02760   0.01774   0.0089   0.0476   1.0000
   7.500   0.7752   0.02889   0.01925   0.0095   0.0445   1.0000
   7.750   0.7971   0.03010   0.02057   0.0101   0.0424   1.0000
   8.000   0.8184   0.03159   0.02211   0.0107   0.0411   1.0000
   8.250   0.8380   0.03386   0.02478   0.0117   0.0398   1.0000
   8.500   0.8550   0.03646   0.02783   0.0129   0.0386   1.0000
   8.750   0.8700   0.03900   0.03077   0.0140   0.0373   1.0000
   9.000   0.8846   0.04111   0.03315   0.0151   0.0360   1.0000
   9.250   0.8993   0.04283   0.03504   0.0160   0.0349   1.0000
   9.500   0.9134   0.04459   0.03688   0.0168   0.0341   1.0000
   9.750   0.9152   0.04831   0.04105   0.0185   0.0336   1.0000
  10.000   0.9087   0.05276   0.04599   0.0204   0.0334   1.0000
  10.250   0.8957   0.05738   0.05102   0.0221   0.0332   1.0000
  10.500   0.8759   0.06181   0.05574   0.0238   0.0332   1.0000
  10.750   0.8521   0.06670   0.06085   0.0239   0.0332   1.0000
  11.000   0.8262   0.07289   0.06722   0.0213   0.0334   1.0000
  11.250   0.7993   0.08097   0.07545   0.0157   0.0336   1.0000
  11.500   0.7736   0.09173   0.08626   0.0075   0.0339   1.0000
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