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NASA SC(2)-1010 AIRFOIL (sc21010-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-1010 AIRFOIL (sc21010-il)
Reynolds number: 100,000
Max Cl/Cd: 49.6 at α=0.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc21010-il-100000-n5.txt
Download as CSV file: xf-sc21010-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.5278   0.09516   0.08945  -0.0446   0.9999   0.0396
 -12.750  -0.5402   0.08896   0.08332  -0.0469   0.9999   0.0394
 -12.500  -0.5599   0.08116   0.07558  -0.0502   0.9999   0.0391
 -12.250  -0.5973   0.07080   0.06527  -0.0554   0.9999   0.0384
 -12.000  -0.6387   0.06441   0.05888  -0.0571   0.9999   0.0379
 -11.750  -0.6698   0.05786   0.05221  -0.0614   0.9999   0.0375
 -11.500  -0.6841   0.05184   0.04585  -0.0654   0.9999   0.0376
 -11.250  -0.6835   0.04641   0.03997  -0.0688   0.9999   0.0379
 -11.000  -0.6717   0.04162   0.03463  -0.0719   0.9999   0.0385
 -10.750  -0.6524   0.03754   0.02996  -0.0747   0.9999   0.0394
 -10.500  -0.6281   0.03420   0.02594  -0.0772   0.9999   0.0408
 -10.250  -0.6059   0.03266   0.02440  -0.0778   0.9999   0.0423
 -10.000  -0.5819   0.03130   0.02289  -0.0786   0.9999   0.0441
  -9.750  -0.5561   0.02962   0.02093  -0.0796   0.9999   0.0460
  -9.500  -0.5292   0.02795   0.01894  -0.0805   0.9999   0.0478
  -9.250  -0.5026   0.02658   0.01741  -0.0812   0.9999   0.0500
  -9.000  -0.4767   0.02573   0.01654  -0.0818   0.9999   0.0528
  -8.750  -0.4494   0.02481   0.01548  -0.0824   0.9999   0.0561
  -8.500  -0.4212   0.02387   0.01438  -0.0831   0.9999   0.0592
  -8.250  -0.3930   0.02310   0.01367  -0.0841   0.9999   0.0634
  -8.000  -0.3644   0.02245   0.01293  -0.0848   0.9999   0.0683
  -7.750  -0.3335   0.02172   0.01221  -0.0862   0.9996   0.0736
  -7.500  -0.2983   0.02118   0.01161  -0.0884   0.9979   0.0820
  -7.250  -0.2620   0.02055   0.01102  -0.0908   0.9965   0.0920
  -7.000  -0.2252   0.02001   0.01051  -0.0934   0.9951   0.1076
  -6.750  -0.1876   0.01947   0.01005  -0.0962   0.9941   0.1310
  -6.500  -0.1506   0.01889   0.00966  -0.0990   0.9929   0.1710
  -6.250  -0.1124   0.01823   0.00940  -0.1023   0.9919   0.2506
  -6.000  -0.0750   0.01771   0.00941  -0.1052   0.9907   0.3672
  -5.750  -0.0404   0.01761   0.00955  -0.1069   0.9885   0.4462
  -5.500  -0.0066   0.01767   0.00970  -0.1083   0.9863   0.4958
  -5.250   0.0269   0.01780   0.00989  -0.1096   0.9843   0.5344
  -5.000   0.0580   0.01794   0.01005  -0.1103   0.9816   0.5630
  -4.750   0.0883   0.01809   0.01020  -0.1108   0.9781   0.5889
  -4.500   0.1181   0.01830   0.01048  -0.1111   0.9750   0.6134
  -4.250   0.1499   0.01853   0.01073  -0.1118   0.9725   0.6360
  -4.000   0.1809   0.01873   0.01094  -0.1124   0.9696   0.6538
  -3.750   0.2076   0.01892   0.01115  -0.1122   0.9653   0.6669
  -3.500   0.2377   0.01910   0.01135  -0.1128   0.9621   0.6795
  -3.250   0.2709   0.01926   0.01152  -0.1140   0.9594   0.6922
  -3.000   0.3045   0.01940   0.01168  -0.1152   0.9563   0.7046
  -2.750   0.3294   0.01957   0.01190  -0.1146   0.9504   0.7142
  -2.500   0.3611   0.01972   0.01210  -0.1155   0.9468   0.7250
  -2.250   0.3947   0.01985   0.01229  -0.1166   0.9438   0.7352
  -2.000   0.4214   0.02001   0.01252  -0.1164   0.9379   0.7446
  -1.750   0.4543   0.02010   0.01267  -0.1175   0.9325   0.7556
  -1.500   0.4894   0.02009   0.01277  -0.1186   0.9285   0.7641
  -1.250   0.5161   0.02020   0.01297  -0.1184   0.9203   0.7736
  -1.000   0.5537   0.02003   0.01291  -0.1199   0.9143   0.7822
  -0.750   0.5912   0.01954   0.01256  -0.1209   0.9013   0.7907
  -0.500   0.6400   0.01819   0.01130  -0.1226   0.8794   0.7997
  -0.250   0.6756   0.01725   0.01047  -0.1222   0.8548   0.8079
   0.000   0.7078   0.01663   0.00993  -0.1216   0.8247   0.8170
   0.250   0.7358   0.01610   0.00944  -0.1200   0.7799   0.8246
   0.500   0.7733   0.01559   0.00864  -0.1199   0.6607   0.8336
   0.750   0.7898   0.01696   0.00852  -0.1164   0.4064   0.8414
   1.000   0.8033   0.01855   0.00919  -0.1140   0.2453   0.8500
   1.250   0.8210   0.01972   0.00980  -0.1123   0.1542   0.8585
   1.500   0.8414   0.02056   0.01041  -0.1109   0.1165   0.8670
   1.750   0.8630   0.02135   0.01110  -0.1098   0.0965   0.8765
   2.000   0.8829   0.02198   0.01174  -0.1081   0.0853   0.8859
   2.250   0.9028   0.02271   0.01246  -0.1066   0.0772   0.8959
   2.500   0.9236   0.02339   0.01319  -0.1052   0.0704   0.9062
   2.750   0.9425   0.02420   0.01403  -0.1034   0.0660   0.9168
   3.000   0.9623   0.02486   0.01478  -0.1018   0.0614   0.9291
   3.250   0.9815   0.02562   0.01553  -0.1002   0.0575   0.9461
   3.500   1.0037   0.02660   0.01661  -0.0992   0.0547   1.0001
   3.750   1.0315   0.02778   0.01788  -0.0993   0.0513   1.0001
   4.000   1.0581   0.02895   0.01901  -0.0995   0.0482   1.0001
   4.250   1.0859   0.03053   0.02063  -0.0998   0.0460   1.0001
   4.500   1.1146   0.03217   0.02249  -0.0999   0.0441   1.0001
   4.750   1.1415   0.03375   0.02423  -0.0999   0.0419   1.0001
   5.000   1.1664   0.03516   0.02571  -0.0998   0.0400   1.0001
   5.250   1.1909   0.03706   0.02767  -0.0997   0.0384   1.0001
   5.500   1.2143   0.03940   0.03044  -0.0989   0.0373   1.0001
   5.750   1.2349   0.04202   0.03348  -0.0979   0.0363   1.0001
   6.000   1.2522   0.04482   0.03668  -0.0965   0.0354   1.0001
   6.250   1.2667   0.04752   0.03973  -0.0948   0.0345   1.0001
   6.500   1.2801   0.04986   0.04233  -0.0931   0.0336   1.0001
   6.750   1.2931   0.05187   0.04448  -0.0916   0.0327   1.0001
   7.000   1.3043   0.05422   0.04693  -0.0901   0.0320   1.0001
   7.250   1.3002   0.05810   0.05135  -0.0864   0.0315   1.0001
   7.500   1.2909   0.06225   0.05599  -0.0825   0.0312   1.0001
   7.750   1.2764   0.06627   0.06039  -0.0783   0.0311   1.0001
   8.000   1.2565   0.07014   0.06458  -0.0740   0.0310   1.0001
   8.250   1.2339   0.07455   0.06928  -0.0707   0.0310   1.0001
   8.500   1.2100   0.07942   0.07442  -0.0687   0.0310   1.0001
   8.750   1.1839   0.08508   0.08032  -0.0681   0.0311   1.0001
   9.000   1.1567   0.09164   0.08711  -0.0695   0.0312   1.0001
   9.250   1.1288   0.09951   0.09516  -0.0731   0.0314   1.0001
   9.500   1.1018   0.10904   0.10485  -0.0793   0.0316   1.0001
   9.750   1.0776   0.12057   0.11648  -0.0878   0.0318   1.0001
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