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NASA SC(2)-0012 AIRFOIL (sc20012-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0012 AIRFOIL (sc20012-il)
Reynolds number: 200,000
Max Cl/Cd: 36 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20012-il-200000.txt
Download as CSV file: xf-sc20012-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0012 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.8387   0.08485   0.08066  -0.0255   1.0000   0.0476
 -12.250  -0.8536   0.07875   0.07450  -0.0282   1.0000   0.0473
 -12.000  -0.8746   0.07269   0.06834  -0.0307   1.0000   0.0469
 -11.750  -0.8985   0.06710   0.06260  -0.0322   1.0000   0.0465
 -11.500  -0.9248   0.06204   0.05735  -0.0321   1.0000   0.0461
 -11.250  -0.9510   0.05760   0.05268  -0.0301   1.0000   0.0458
 -11.000  -0.9731   0.05356   0.04836  -0.0268   1.0000   0.0456
 -10.750  -0.9876   0.04924   0.04368  -0.0239   1.0000   0.0454
 -10.500  -0.9948   0.04511   0.03915  -0.0212   1.0000   0.0454
 -10.250  -0.9952   0.04142   0.03503  -0.0187   1.0000   0.0457
 -10.000  -0.9900   0.03819   0.03136  -0.0164   1.0000   0.0463
  -9.750  -0.9805   0.03547   0.02816  -0.0144   1.0000   0.0471
  -9.500  -0.9671   0.03291   0.02522  -0.0127   1.0000   0.0482
  -9.250  -0.9462   0.03123   0.02355  -0.0123   1.0000   0.0495
  -9.000  -0.9249   0.03020   0.02249  -0.0116   1.0000   0.0514
  -8.750  -0.9049   0.02892   0.02096  -0.0106   1.0000   0.0537
  -8.500  -0.8847   0.02722   0.01900  -0.0096   1.0000   0.0560
  -8.250  -0.8616   0.02605   0.01789  -0.0092   1.0000   0.0583
  -8.000  -0.8389   0.02506   0.01680  -0.0085   1.0000   0.0610
  -7.750  -0.8166   0.02412   0.01563  -0.0075   1.0000   0.0640
  -7.500  -0.7933   0.02293   0.01457  -0.0072   1.0000   0.0674
  -7.250  -0.7706   0.02226   0.01384  -0.0064   1.0000   0.0711
  -7.000  -0.7482   0.02128   0.01278  -0.0056   1.0000   0.0748
  -6.750  -0.7265   0.02057   0.01216  -0.0047   1.0000   0.0786
  -6.500  -0.7057   0.02006   0.01159  -0.0035   1.0000   0.0827
  -6.250  -0.6866   0.01921   0.01075  -0.0021   1.0000   0.0865
  -6.000  -0.6703   0.01869   0.01031  -0.0003   1.0000   0.0903
  -5.750  -0.6577   0.01836   0.00996   0.0023   1.0000   0.0941
  -5.500  -0.6477   0.01800   0.00957   0.0051   1.0000   0.0975
  -5.250  -0.6229   0.01736   0.00903   0.0049   0.9976   0.1031
  -5.000  -0.5851   0.01678   0.00843   0.0025   0.9936   0.1108
  -4.750  -0.5502   0.01608   0.00783   0.0005   0.9884   0.1206
  -4.500  -0.5142   0.01538   0.00722  -0.0017   0.9841   0.1347
  -4.250  -0.4800   0.01462   0.00665  -0.0036   0.9794   0.1592
  -4.000  -0.4485   0.01362   0.00608  -0.0052   0.9741   0.2237
  -3.750  -0.4196   0.01203   0.00549  -0.0068   0.9702   0.4080
  -3.500  -0.3960   0.01113   0.00565  -0.0060   0.9643   0.6217
  -3.250  -0.3633   0.01121   0.00581  -0.0066   0.9588   0.6868
  -3.000  -0.3283   0.01130   0.00591  -0.0077   0.9550   0.7198
  -2.750  -0.2982   0.01143   0.00604  -0.0078   0.9495   0.7433
  -2.500  -0.2687   0.01155   0.00617  -0.0077   0.9440   0.7627
  -2.250  -0.2371   0.01166   0.00627  -0.0080   0.9396   0.7794
  -2.000  -0.2072   0.01179   0.00642  -0.0078   0.9352   0.7958
  -1.750  -0.1823   0.01196   0.00659  -0.0067   0.9287   0.8114
  -1.500  -0.1550   0.01210   0.00673  -0.0061   0.9240   0.8264
  -1.250  -0.1266   0.01225   0.00691  -0.0054   0.9203   0.8385
  -1.000  -0.1021   0.01241   0.00709  -0.0042   0.9144   0.8504
  -0.500  -0.0505   0.01265   0.00736  -0.0022   0.9040   0.8719
  -0.250  -0.0253   0.01271   0.00740  -0.0013   0.8985   0.8827
   0.000   0.0000   0.01282   0.00754   0.0000   0.8906   0.8906
   0.250   0.0253   0.01271   0.00740   0.0013   0.8826   0.8985
   0.500   0.0505   0.01265   0.00736   0.0022   0.8719   0.9040
   0.750   0.0776   0.01253   0.00720   0.0032   0.8631   0.9084
   1.000   0.1021   0.01241   0.00709   0.0042   0.8505   0.9144
   1.250   0.1266   0.01225   0.00691   0.0054   0.8385   0.9203
   1.500   0.1550   0.01210   0.00673   0.0061   0.8264   0.9241
   1.750   0.1823   0.01196   0.00659   0.0067   0.8114   0.9287
   2.000   0.2071   0.01179   0.00641   0.0078   0.7958   0.9352
   2.250   0.2371   0.01166   0.00627   0.0080   0.7793   0.9396
   2.500   0.2687   0.01155   0.00617   0.0077   0.7626   0.9440
   2.750   0.2982   0.01143   0.00604   0.0078   0.7434   0.9495
   3.000   0.3283   0.01130   0.00591   0.0077   0.7198   0.9551
   3.250   0.3633   0.01121   0.00581   0.0066   0.6869   0.9589
   3.500   0.3960   0.01113   0.00565   0.0060   0.6220   0.9643
   3.750   0.4196   0.01203   0.00548   0.0068   0.4081   0.9703
   4.000   0.4485   0.01362   0.00608   0.0052   0.2236   0.9741
   4.250   0.4800   0.01462   0.00665   0.0036   0.1592   0.9795
   4.500   0.5142   0.01538   0.00722   0.0017   0.1347   0.9842
   4.750   0.5503   0.01608   0.00782  -0.0005   0.1206   0.9884
   5.000   0.5852   0.01678   0.00843  -0.0025   0.1108   0.9937
   5.250   0.6230   0.01736   0.00903  -0.0049   0.1031   0.9976
   5.500   0.6476   0.01799   0.00957  -0.0051   0.0975   1.0000
   5.750   0.6576   0.01836   0.00996  -0.0022   0.0942   1.0000
   6.000   0.6701   0.01868   0.01030   0.0003   0.0903   1.0000
   6.250   0.6865   0.01921   0.01075   0.0021   0.0865   1.0000
   6.500   0.7056   0.02006   0.01159   0.0035   0.0827   1.0000
   6.750   0.7265   0.02057   0.01215   0.0047   0.0786   1.0000
   7.000   0.7482   0.02128   0.01278   0.0056   0.0748   1.0000
   7.250   0.7706   0.02226   0.01384   0.0064   0.0711   1.0000
   7.500   0.7934   0.02293   0.01457   0.0072   0.0674   1.0000
   7.750   0.8166   0.02412   0.01563   0.0075   0.0640   1.0000
   8.000   0.8389   0.02506   0.01680   0.0085   0.0610   1.0000
   8.250   0.8616   0.02604   0.01789   0.0092   0.0582   1.0000
   8.500   0.8847   0.02722   0.01900   0.0096   0.0560   1.0000
   8.750   0.9050   0.02892   0.02096   0.0106   0.0537   1.0000
   9.000   0.9250   0.03020   0.02248   0.0116   0.0513   1.0000
   9.250   0.9463   0.03123   0.02354   0.0123   0.0495   1.0000
   9.500   0.9672   0.03292   0.02522   0.0127   0.0482   1.0000
   9.750   0.9806   0.03547   0.02816   0.0143   0.0471   1.0000
  10.000   0.9902   0.03820   0.03137   0.0164   0.0463   1.0000
  10.250   0.9954   0.04143   0.03504   0.0186   0.0457   1.0000
  10.500   0.9950   0.04513   0.03916   0.0211   0.0454   1.0000
  10.750   0.9877   0.04927   0.04371   0.0239   0.0454   1.0000
  11.000   0.9734   0.05359   0.04839   0.0267   0.0456   1.0000
  11.250   0.9512   0.05766   0.05273   0.0300   0.0458   1.0000
  11.500   0.9250   0.06211   0.05742   0.0320   0.0461   1.0000
  11.750   0.8996   0.06711   0.06261   0.0321   0.0465   1.0000
  12.000   0.8750   0.07278   0.06843   0.0305   0.0469   1.0000
  12.250   0.8539   0.07888   0.07463   0.0279   0.0473   1.0000
  12.500   0.8400   0.08486   0.08066   0.0253   0.0476   1.0000
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