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NASA SC(2)-0012 AIRFOIL (sc20012-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0012 AIRFOIL (sc20012-il)
Reynolds number: 500,000
Max Cl/Cd: 53.69 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20012-il-500000.txt
Download as CSV file: xf-sc20012-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.500  -1.0628   0.09915   0.09601  -0.0086   1.0000   0.0225
 -16.250  -1.1008   0.08685   0.08347  -0.0170   1.0000   0.0224
 -16.000  -1.1327   0.07699   0.07339  -0.0233   1.0000   0.0223
 -15.750  -1.1585   0.06922   0.06540  -0.0278   1.0000   0.0223
 -15.500  -1.1795   0.06293   0.05890  -0.0307   1.0000   0.0223
 -15.250  -1.1965   0.05770   0.05346  -0.0325   1.0000   0.0223
 -15.000  -1.2100   0.05329   0.04884  -0.0335   1.0000   0.0224
 -14.750  -1.2201   0.04951   0.04487  -0.0338   1.0000   0.0224
 -14.500  -1.2297   0.04592   0.04107  -0.0335   1.0000   0.0225
 -14.250  -1.2378   0.04248   0.03744  -0.0327   1.0000   0.0227
 -14.000  -1.2406   0.03969   0.03451  -0.0316   1.0000   0.0228
 -13.750  -1.2390   0.03750   0.03219  -0.0304   1.0000   0.0230
 -13.500  -1.2346   0.03567   0.03027  -0.0291   1.0000   0.0232
 -13.250  -1.2285   0.03407   0.02858  -0.0277   1.0000   0.0235
 -13.000  -1.2212   0.03263   0.02705  -0.0261   1.0000   0.0237
 -12.750  -1.2129   0.03131   0.02563  -0.0245   1.0000   0.0240
 -12.500  -1.2039   0.03007   0.02428  -0.0226   1.0000   0.0243
 -12.250  -1.1941   0.02891   0.02301  -0.0206   1.0000   0.0246
 -12.000  -1.1833   0.02781   0.02180  -0.0186   1.0000   0.0250
 -11.750  -1.1697   0.02674   0.02061  -0.0170   1.0000   0.0254
 -11.500  -1.1539   0.02574   0.01949  -0.0156   1.0000   0.0259
 -11.250  -1.1367   0.02485   0.01846  -0.0144   1.0000   0.0263
 -11.000  -1.1214   0.02350   0.01705  -0.0130   1.0000   0.0269
 -10.750  -1.1033   0.02264   0.01617  -0.0119   1.0000   0.0275
 -10.500  -1.0832   0.02200   0.01551  -0.0110   1.0000   0.0283
 -10.250  -1.0624   0.02137   0.01483  -0.0101   1.0000   0.0292
 -10.000  -1.0411   0.02074   0.01411  -0.0093   1.0000   0.0302
  -9.750  -1.0209   0.01989   0.01319  -0.0083   1.0000   0.0312
  -9.500  -1.0002   0.01917   0.01249  -0.0075   1.0000   0.0323
  -9.250  -0.9775   0.01868   0.01197  -0.0068   1.0000   0.0337
  -9.000  -0.9542   0.01821   0.01143  -0.0062   1.0000   0.0353
  -8.750  -0.9331   0.01746   0.01068  -0.0053   1.0000   0.0370
  -8.500  -0.9094   0.01707   0.01029  -0.0048   1.0000   0.0389
  -8.250  -0.8850   0.01673   0.00990  -0.0043   1.0000   0.0409
  -8.000  -0.8633   0.01608   0.00927  -0.0035   1.0000   0.0431
  -7.750  -0.8392   0.01576   0.00896  -0.0030   1.0000   0.0453
  -7.500  -0.8146   0.01553   0.00867  -0.0024   1.0000   0.0475
  -7.250  -0.7939   0.01492   0.00810  -0.0014   1.0000   0.0500
  -7.000  -0.7719   0.01463   0.00783  -0.0005   1.0000   0.0524
  -6.750  -0.7515   0.01440   0.00758   0.0009   1.0000   0.0545
  -6.500  -0.7187   0.01377   0.00697  -0.0007   0.9957   0.0576
  -6.250  -0.6823   0.01337   0.00658  -0.0028   0.9896   0.0608
  -5.750  -0.6130   0.01254   0.00577  -0.0062   0.9706   0.0686
  -5.500  -0.5815   0.01227   0.00548  -0.0071   0.9567   0.0724
  -5.250  -0.5550   0.01188   0.00508  -0.0068   0.9403   0.0769
  -5.000  -0.5301   0.01162   0.00481  -0.0062   0.9244   0.0815
  -4.750  -0.5054   0.01134   0.00451  -0.0055   0.9106   0.0873
  -4.500  -0.4804   0.01110   0.00425  -0.0048   0.8991   0.0955
  -4.250  -0.4549   0.01079   0.00399  -0.0044   0.8884   0.1089
  -4.000  -0.4298   0.01044   0.00372  -0.0039   0.8800   0.1320
  -3.750  -0.4042   0.01003   0.00349  -0.0036   0.8719   0.1703
  -3.500  -0.3795   0.00956   0.00325  -0.0032   0.8652   0.2284
  -3.250  -0.3549   0.00897   0.00301  -0.0029   0.8585   0.3117
  -3.000  -0.3317   0.00820   0.00273  -0.0025   0.8519   0.4329
  -2.750  -0.3098   0.00743   0.00256  -0.0015   0.8464   0.5781
  -2.500  -0.2832   0.00731   0.00265  -0.0011   0.8415   0.6498
  -2.250  -0.2546   0.00732   0.00267  -0.0011   0.8370   0.6781
  -2.000  -0.2261   0.00733   0.00268  -0.0011   0.8325   0.6962
  -1.750  -0.1977   0.00736   0.00270  -0.0010   0.8283   0.7100
  -1.500  -0.1692   0.00738   0.00272  -0.0010   0.8242   0.7217
  -1.250  -0.1404   0.00739   0.00273  -0.0010   0.8190   0.7336
  -1.000  -0.1124   0.00739   0.00274  -0.0008   0.8121   0.7442
  -0.750  -0.0846   0.00743   0.00277  -0.0005   0.8053   0.7560
  -0.500  -0.0563   0.00745   0.00280  -0.0004   0.7983   0.7679
  -0.250  -0.0284   0.00743   0.00278  -0.0001   0.7910   0.7757
   0.000   0.0000   0.00745   0.00280   0.0000   0.7837   0.7837
   0.250   0.0284   0.00743   0.00278   0.0001   0.7755   0.7910
   0.500   0.0563   0.00745   0.00280   0.0004   0.7678   0.7983
   0.750   0.0846   0.00743   0.00277   0.0005   0.7563   0.8054
   1.000   0.1123   0.00739   0.00274   0.0008   0.7443   0.8123
   1.250   0.1403   0.00739   0.00273   0.0011   0.7335   0.8191
   1.500   0.1692   0.00738   0.00272   0.0010   0.7218   0.8242
   1.750   0.1977   0.00736   0.00270   0.0010   0.7100   0.8283
   2.000   0.2261   0.00733   0.00268   0.0011   0.6963   0.8325
   2.250   0.2546   0.00732   0.00267   0.0011   0.6781   0.8370
   2.500   0.2832   0.00731   0.00265   0.0011   0.6499   0.8415
   2.750   0.3098   0.00744   0.00256   0.0015   0.5776   0.8464
   3.000   0.3317   0.00820   0.00273   0.0025   0.4332   0.8519
   3.250   0.3548   0.00898   0.00301   0.0029   0.3111   0.8585
   3.500   0.3795   0.00956   0.00325   0.0032   0.2283   0.8651
   3.750   0.4042   0.01003   0.00349   0.0036   0.1702   0.8719
   4.000   0.4298   0.01044   0.00372   0.0039   0.1319   0.8800
   4.250   0.4549   0.01079   0.00399   0.0044   0.1088   0.8884
   4.500   0.4804   0.01110   0.00425   0.0048   0.0955   0.8991
   4.750   0.5054   0.01134   0.00450   0.0055   0.0874   0.9106
   5.000   0.5301   0.01162   0.00481   0.0062   0.0815   0.9244
   5.250   0.5550   0.01187   0.00508   0.0068   0.0768   0.9403
   5.500   0.5816   0.01227   0.00548   0.0071   0.0724   0.9567
   5.750   0.6131   0.01254   0.00577   0.0062   0.0686   0.9706
   6.000   0.6454   0.01311   0.00628   0.0049   0.0638   0.9822
   6.250   0.6824   0.01337   0.00658   0.0028   0.0608   0.9896
   6.500   0.7188   0.01377   0.00696   0.0007   0.0575   0.9957
   6.750   0.7514   0.01440   0.00758  -0.0008   0.0545   1.0000
   7.000   0.7718   0.01463   0.00783   0.0005   0.0524   1.0000
   7.250   0.7939   0.01491   0.00810   0.0014   0.0500   1.0000
   7.500   0.8147   0.01553   0.00867   0.0024   0.0475   1.0000
   7.750   0.8393   0.01576   0.00896   0.0030   0.0453   1.0000
   8.000   0.8633   0.01608   0.00927   0.0035   0.0431   1.0000
   8.250   0.8851   0.01673   0.00990   0.0043   0.0409   1.0000
   8.500   0.9095   0.01707   0.01029   0.0048   0.0388   1.0000
   8.750   0.9332   0.01746   0.01068   0.0053   0.0370   1.0000
   9.000   0.9543   0.01821   0.01143   0.0062   0.0353   1.0000
   9.250   0.9776   0.01867   0.01197   0.0068   0.0337   1.0000
   9.500   1.0003   0.01917   0.01249   0.0074   0.0323   1.0000
   9.750   1.0211   0.01989   0.01319   0.0083   0.0312   1.0000
  10.000   1.0412   0.02074   0.01410   0.0093   0.0302   1.0000
  10.250   1.0626   0.02137   0.01483   0.0101   0.0292   1.0000
  10.500   1.0834   0.02200   0.01551   0.0109   0.0283   1.0000
  10.750   1.1035   0.02264   0.01617   0.0118   0.0275   1.0000
  11.000   1.1217   0.02350   0.01705   0.0129   0.0269   1.0000
  11.250   1.1370   0.02484   0.01845   0.0143   0.0263   1.0000
  11.500   1.1543   0.02574   0.01948   0.0155   0.0259   1.0000
  11.750   1.1700   0.02675   0.02062   0.0169   0.0254   1.0000
  12.000   1.1837   0.02781   0.02180   0.0185   0.0250   1.0000
  12.250   1.1946   0.02891   0.02301   0.0205   0.0246   1.0000
  12.500   1.2044   0.03008   0.02429   0.0225   0.0243   1.0000
  12.750   1.2136   0.03130   0.02562   0.0243   0.0240   1.0000
  13.000   1.2219   0.03263   0.02704   0.0260   0.0237   1.0000
  13.250   1.2293   0.03406   0.02857   0.0276   0.0235   1.0000
  13.500   1.2354   0.03565   0.03025   0.0290   0.0232   1.0000
  13.750   1.2398   0.03750   0.03219   0.0303   0.0230   1.0000
  14.000   1.2414   0.03971   0.03452   0.0314   0.0228   1.0000
  14.250   1.2387   0.04247   0.03744   0.0325   0.0227   1.0000
  14.500   1.2304   0.04596   0.04111   0.0333   0.0225   1.0000
  14.750   1.2211   0.04952   0.04487   0.0336   0.0224   1.0000
  15.000   1.2111   0.05329   0.04885   0.0333   0.0224   1.0000
  15.250   1.1977   0.05770   0.05346   0.0323   0.0223   1.0000
  15.500   1.1807   0.06295   0.05892   0.0305   0.0223   1.0000
  15.750   1.1596   0.06926   0.06544   0.0275   0.0223   1.0000
  16.000   1.1338   0.07707   0.07347   0.0230   0.0223   1.0000
  16.250   1.1018   0.08699   0.08362   0.0166   0.0224   1.0000
  16.500   1.0632   0.09944   0.09630   0.0081   0.0225   1.0000
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