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NASA SC(2)-0410 AIRFOIL (sc20410-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0410 AIRFOIL (sc20410-il)
Reynolds number: 100,000
Max Cl/Cd: 29.31 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20410-il-100000-n5.txt
Download as CSV file: xf-sc20410-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.7083   0.10090   0.09518  -0.0161   1.0000   0.0343
 -11.500  -0.7285   0.08971   0.08398  -0.0231   1.0000   0.0341
 -11.250  -0.7559   0.07911   0.07329  -0.0310   1.0000   0.0338
 -11.000  -0.7831   0.07113   0.06517  -0.0365   1.0000   0.0336
 -10.750  -0.8079   0.06495   0.05882  -0.0396   1.0000   0.0334
 -10.500  -0.8303   0.06003   0.05369  -0.0407   1.0000   0.0334
 -10.250  -0.8481   0.05551   0.04890  -0.0413   1.0000   0.0334
 -10.000  -0.8587   0.05086   0.04385  -0.0415   1.0000   0.0337
  -9.750  -0.8638   0.04625   0.03863  -0.0414   1.0000   0.0344
  -9.500  -0.8508   0.04426   0.03660  -0.0412   1.0000   0.0352
  -9.250  -0.8368   0.04238   0.03458  -0.0409   1.0000   0.0362
  -9.000  -0.8223   0.04017   0.03213  -0.0406   1.0000   0.0373
  -8.750  -0.8070   0.03755   0.02917  -0.0403   1.0000   0.0383
  -8.500  -0.7897   0.03495   0.02617  -0.0398   1.0000   0.0394
  -8.250  -0.7704   0.03255   0.02335  -0.0393   1.0000   0.0408
  -8.000  -0.7497   0.03060   0.02117  -0.0388   1.0000   0.0422
  -7.750  -0.7282   0.02946   0.02002  -0.0385   1.0000   0.0442
  -7.500  -0.7060   0.02829   0.01870  -0.0380   1.0000   0.0470
  -7.250  -0.6832   0.02696   0.01709  -0.0374   1.0000   0.0499
  -7.000  -0.6612   0.02564   0.01580  -0.0368   1.0000   0.0523
  -6.750  -0.6384   0.02474   0.01489  -0.0364   1.0000   0.0559
  -6.500  -0.6149   0.02384   0.01379  -0.0357   1.0000   0.0601
  -6.250  -0.5924   0.02282   0.01286  -0.0353   1.0000   0.0642
  -6.000  -0.5690   0.02204   0.01205  -0.0348   1.0000   0.0692
  -5.750  -0.5456   0.02119   0.01117  -0.0343   1.0000   0.0742
  -5.500  -0.5219   0.02042   0.01044  -0.0340   1.0000   0.0802
  -5.250  -0.4975   0.01977   0.00971  -0.0336   1.0000   0.0862
  -5.000  -0.4731   0.01898   0.00902  -0.0335   1.0000   0.0942
  -4.750  -0.4479   0.01832   0.00837  -0.0334   1.0000   0.1034
  -4.500  -0.4222   0.01771   0.00781  -0.0335   1.0000   0.1165
  -4.250  -0.3960   0.01703   0.00730  -0.0338   1.0000   0.1386
  -4.000  -0.3688   0.01624   0.00682  -0.0344   1.0000   0.1858
  -3.750  -0.3383   0.01499   0.00627  -0.0364   1.0000   0.3179
  -3.500  -0.3153   0.01417   0.00670  -0.0356   1.0000   0.5266
  -3.250  -0.2942   0.01450   0.00719  -0.0335   1.0000   0.6146
  -3.000  -0.2698   0.01477   0.00741  -0.0325   1.0000   0.6507
  -2.750  -0.2455   0.01505   0.00762  -0.0315   1.0000   0.6757
  -2.500  -0.2253   0.01546   0.00802  -0.0293   1.0000   0.6969
  -2.250  -0.2064   0.01595   0.00851  -0.0268   1.0000   0.7191
  -2.000  -0.1886   0.01641   0.00897  -0.0240   1.0000   0.7381
  -1.750  -0.1736   0.01680   0.00939  -0.0206   1.0000   0.7509
  -1.500  -0.1547   0.01703   0.00962  -0.0185   1.0000   0.7616
  -1.250  -0.1299   0.01716   0.00970  -0.0181   1.0000   0.7722
  -1.000  -0.1108   0.01730   0.00985  -0.0162   1.0000   0.7787
  -0.750  -0.0825   0.01736   0.00988  -0.0169   0.9997   0.7861
  -0.500  -0.0466   0.01736   0.00987  -0.0188   0.9946   0.7891
  -0.250  -0.0109   0.01735   0.00986  -0.0207   0.9884   0.7919
   0.000   0.0272   0.01737   0.00989  -0.0232   0.9834   0.7953
   0.250   0.0639   0.01734   0.00989  -0.0254   0.9763   0.7990
   0.500   0.1071   0.01728   0.00985  -0.0290   0.9687   0.8019
   0.750   0.1495   0.01715   0.00979  -0.0318   0.9583   0.8038
   1.000   0.1916   0.01695   0.00967  -0.0344   0.9454   0.8057
   1.250   0.2387   0.01659   0.00938  -0.0377   0.9287   0.8074
   1.500   0.2782   0.01620   0.00907  -0.0392   0.9030   0.8093
   1.750   0.3163   0.01584   0.00877  -0.0404   0.8723   0.8118
   2.000   0.3532   0.01553   0.00848  -0.0412   0.8303   0.8144
   2.250   0.3874   0.01536   0.00822  -0.0416   0.7692   0.8167
   2.500   0.4152   0.01538   0.00800  -0.0404   0.6734   0.8187
   2.750   0.4363   0.01613   0.00786  -0.0382   0.4798   0.8210
   3.000   0.4562   0.01726   0.00817  -0.0369   0.3146   0.8237
   3.250   0.4797   0.01823   0.00854  -0.0367   0.2035   0.8262
   3.500   0.5059   0.01897   0.00897  -0.0369   0.1523   0.8288
   3.750   0.5337   0.01960   0.00947  -0.0373   0.1256   0.8315
   4.000   0.5579   0.02015   0.00998  -0.0366   0.1103   0.8338
   4.250   0.5828   0.02069   0.01052  -0.0361   0.0986   0.8365
   4.500   0.6081   0.02135   0.01117  -0.0358   0.0906   0.8395
   4.750   0.6347   0.02198   0.01183  -0.0358   0.0829   0.8424
   5.000   0.6616   0.02280   0.01266  -0.0360   0.0768   0.8453
   5.250   0.6875   0.02350   0.01341  -0.0358   0.0709   0.8479
   5.500   0.7117   0.02438   0.01429  -0.0353   0.0660   0.8504
   5.750   0.7377   0.02517   0.01522  -0.0350   0.0610   0.8533
   6.000   0.7632   0.02605   0.01607  -0.0350   0.0568   0.8566
   6.250   0.7902   0.02723   0.01742  -0.0350   0.0530   0.8601
   6.500   0.8152   0.02817   0.01853  -0.0346   0.0493   0.8634
   6.750   0.8386   0.02923   0.01959  -0.0342   0.0469   0.8668
   7.000   0.8633   0.03090   0.02151  -0.0337   0.0449   0.8704
   7.250   0.8881   0.03267   0.02362  -0.0334   0.0427   0.8741
   7.500   0.9113   0.03409   0.02528  -0.0330   0.0406   0.8777
   7.750   0.9324   0.03521   0.02649  -0.0324   0.0390   0.8813
   8.000   0.9520   0.03733   0.02893  -0.0315   0.0376   0.8855
   8.250   0.9689   0.04039   0.03256  -0.0304   0.0365   0.8901
   8.500   0.9807   0.04361   0.03633  -0.0287   0.0357   0.8946
   8.750   0.9891   0.04719   0.04042  -0.0270   0.0351   0.8997
   9.000   0.9937   0.05126   0.04499  -0.0255   0.0346   0.9052
   9.250   0.9915   0.05547   0.04966  -0.0234   0.0343   0.9107
   9.500   0.9849   0.05998   0.05459  -0.0217   0.0340   0.9170
   9.750   0.9714   0.06469   0.05965  -0.0201   0.0338   0.9241
  10.250   0.9116   0.07697   0.07253  -0.0199   0.0342   0.9478
  10.500   0.8658   0.08967   0.08546  -0.0292   0.0351   0.9980
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