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NASA SC(2)-1010 AIRFOIL (sc21010-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-1010 AIRFOIL (sc21010-il)
Reynolds number: 100,000
Max Cl/Cd: 48.75 at α=1.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc21010-il-100000.txt
Download as CSV file: xf-sc21010-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-1010 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4713   0.09711   0.09177  -0.0323   0.9999   0.1508
 -11.000  -0.5097   0.09510   0.08994  -0.0333   0.9999   0.1569
 -10.750  -0.5475   0.09193   0.08697  -0.0333   0.9999   0.1586
 -10.500  -0.5041   0.08896   0.08389  -0.0292   0.9999   0.1624
 -10.250  -0.5098   0.08690   0.08189  -0.0268   0.9999   0.1667
 -10.000  -0.5999   0.05598   0.05009  -0.0640   0.9999   0.0964
  -9.750  -0.5781   0.04536   0.03850  -0.0718   0.9999   0.0826
  -9.500  -0.5525   0.04074   0.03342  -0.0751   0.9999   0.0825
  -9.250  -0.5224   0.03634   0.02847  -0.0787   0.9999   0.0838
  -9.000  -0.4926   0.03288   0.02464  -0.0811   0.9999   0.0849
  -8.750  -0.4633   0.03048   0.02201  -0.0826   0.9999   0.0869
  -8.500  -0.4348   0.02894   0.02029  -0.0837   0.9999   0.0914
  -8.250  -0.4025   0.02734   0.01822  -0.0851   0.9999   0.0960
  -8.000  -0.3713   0.02541   0.01617  -0.0865   0.9999   0.1006
  -7.750  -0.3418   0.02442   0.01509  -0.0873   0.9999   0.1083
  -7.500  -0.3109   0.02310   0.01371  -0.0882   0.9999   0.1155
  -7.250  -0.2807   0.02236   0.01285  -0.0890   0.9999   0.1269
  -7.000  -0.2495   0.02130   0.01195  -0.0900   0.9999   0.1412
  -6.750  -0.2157   0.02028   0.01119  -0.0918   0.9999   0.1656
  -6.500  -0.1747   0.01905   0.01040  -0.0954   0.9999   0.2249
  -6.250  -0.1267   0.01775   0.01035  -0.1007   0.9999   0.4469
  -6.000  -0.1014   0.01802   0.01078  -0.1001   0.9999   0.5244
  -5.750  -0.0787   0.01843   0.01122  -0.0988   0.9999   0.5714
  -5.500  -0.0590   0.01887   0.01171  -0.0967   0.9999   0.6031
  -5.250  -0.0407   0.01932   0.01221  -0.0943   0.9999   0.6278
  -5.000  -0.0228   0.01980   0.01271  -0.0919   0.9999   0.6511
  -4.750  -0.0027   0.02022   0.01311  -0.0901   0.9999   0.6732
  -4.500   0.0149   0.02063   0.01354  -0.0878   0.9999   0.6912
  -4.250   0.0321   0.02104   0.01396  -0.0853   0.9999   0.7087
  -4.000   0.0471   0.02146   0.01442  -0.0823   0.9999   0.7266
  -3.750   0.0625   0.02184   0.01482  -0.0795   0.9999   0.7445
  -3.500   0.0800   0.02215   0.01515  -0.0773   0.9999   0.7612
  -3.250   0.0997   0.02240   0.01540  -0.0759   0.9999   0.7766
  -3.000   0.1204   0.02264   0.01564  -0.0747   0.9999   0.7916
  -2.750   0.1418   0.02285   0.01586  -0.0738   0.9999   0.8061
  -2.500   0.1641   0.02306   0.01609  -0.0732   0.9999   0.8205
  -2.250   0.1864   0.02327   0.01631  -0.0726   0.9999   0.8352
  -2.000   0.2088   0.02346   0.01654  -0.0721   0.9999   0.8501
  -1.750   0.2313   0.02364   0.01676  -0.0717   0.9999   0.8649
  -1.500   0.2538   0.02383   0.01699  -0.0714   0.9999   0.8801
  -1.250   0.2760   0.02400   0.01722  -0.0710   0.9999   0.8960
  -1.000   0.2979   0.02418   0.01746  -0.0707   0.9999   0.9130
  -0.750   0.3195   0.02437   0.01772  -0.0704   0.9999   0.9320
  -0.500   0.3537   0.02438   0.01784  -0.0725   0.9907   0.9533
  -0.250   0.3923   0.02432   0.01789  -0.0754   0.9737   0.9971
   0.000   0.4571   0.02464   0.01832  -0.0832   0.9587   1.0001
   0.250   0.5286   0.02399   0.01781  -0.0905   0.9320   1.0001
   0.500   0.5976   0.02274   0.01675  -0.0965   0.9065   1.0001
   0.750   0.6684   0.02050   0.01471  -0.1011   0.8784   1.0001
   1.000   0.7290   0.01798   0.01242  -0.1034   0.8474   1.0001
   1.250   0.7741   0.01588   0.01049  -0.1028   0.7953   1.0001
   1.500   0.8002   0.01669   0.00871  -0.0979   0.3093   1.0001
   1.750   0.8139   0.01949   0.01024  -0.0961   0.1633   1.0001
   2.000   0.8387   0.02110   0.01158  -0.0958   0.1358   1.0001
   2.250   0.8669   0.02257   0.01290  -0.0962   0.1198   1.0001
   2.500   0.8983   0.02436   0.01444  -0.0971   0.1088   1.0001
   2.750   0.9308   0.02559   0.01579  -0.0979   0.0998   1.0001
   3.000   0.9659   0.02770   0.01778  -0.0994   0.0934   1.0001
   3.250   0.9991   0.02929   0.01957  -0.1001   0.0879   1.0001
   3.500   1.0309   0.03115   0.02143  -0.1010   0.0827   1.0001
   3.750   1.0640   0.03434   0.02477  -0.1020   0.0802   1.0001
   4.000   1.0918   0.03648   0.02737  -0.1015   0.0784   1.0001
   4.250   1.1174   0.03886   0.03019  -0.1009   0.0758   1.0001
   4.500   1.1411   0.04196   0.03375  -0.1000   0.0749   1.0001
   4.750   1.1611   0.04581   0.03810  -0.0986   0.0758   1.0001
   5.000   1.1782   0.05021   0.04293  -0.0971   0.0776   1.0001
   5.250   1.1934   0.05513   0.04815  -0.0958   0.0794   1.0001
   5.500   1.1126   0.05257   0.04704  -0.0776   0.0917   1.0001
   6.000   1.1807   0.08939   0.08499  -0.0885   0.1699   1.0001
   6.250   1.1011   0.09196   0.08814  -0.0842   0.1664   1.0001
   6.500   1.0620   0.09754   0.09383  -0.0842   0.1642   1.0001
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