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NASA SC(2)-1010 AIRFOIL (sc21010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-1010 AIRFOIL (sc21010-il)
Reynolds number: 1,000,000
Max Cl/Cd: 115.25 at α=-1.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc21010-il-1000000.txt
Download as CSV file: xf-sc21010-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.250  -0.8842   0.07398   0.07159  -0.0572   0.9999   0.0148
 -17.000  -0.9250   0.06216   0.05957  -0.0654   0.9999   0.0147
 -16.750  -0.9487   0.05422   0.05146  -0.0711   0.9999   0.0147
 -16.500  -0.9657   0.04806   0.04514  -0.0755   0.9999   0.0147
 -16.250  -0.9782   0.04336   0.04031  -0.0783   0.9999   0.0148
 -16.000  -0.9899   0.03971   0.03655  -0.0794   0.9999   0.0149
 -15.750  -1.0068   0.03695   0.03369  -0.0781   0.9999   0.0149
 -15.500  -1.0320   0.03498   0.03166  -0.0740   0.9999   0.0149
 -15.250  -1.0384   0.03275   0.02933  -0.0735   0.9999   0.0150
 -15.000  -1.0223   0.03060   0.02702  -0.0767   0.9992   0.0151
 -14.750  -0.9929   0.02860   0.02484  -0.0816   0.9979   0.0153
 -14.500  -0.9681   0.02467   0.02059  -0.0873   0.9965   0.0156
 -14.250  -0.9384   0.02266   0.01843  -0.0910   0.9956   0.0160
 -14.000  -0.9069   0.02148   0.01716  -0.0938   0.9949   0.0163
 -13.750  -0.8747   0.02053   0.01614  -0.0963   0.9943   0.0166
 -13.500  -0.8423   0.01966   0.01519  -0.0987   0.9938   0.0170
 -13.250  -0.8120   0.01882   0.01427  -0.1005   0.9924   0.0174
 -13.000  -0.7804   0.01802   0.01337  -0.1025   0.9912   0.0178
 -12.750  -0.7479   0.01727   0.01254  -0.1045   0.9901   0.0182
 -12.500  -0.7150   0.01661   0.01180  -0.1065   0.9890   0.0186
 -12.250  -0.6818   0.01610   0.01121  -0.1084   0.9881   0.0189
 -12.000  -0.6474   0.01475   0.00978  -0.1113   0.9875   0.0198
 -11.750  -0.6135   0.01422   0.00922  -0.1134   0.9868   0.0205
 -11.500  -0.5793   0.01373   0.00870  -0.1154   0.9861   0.0212
 -11.250  -0.5448   0.01326   0.00819  -0.1174   0.9856   0.0219
 -11.000  -0.5101   0.01284   0.00772  -0.1194   0.9850   0.0227
 -10.750  -0.4748   0.01226   0.00707  -0.1217   0.9846   0.0235
 -10.500  -0.4393   0.01169   0.00649  -0.1240   0.9843   0.0249
 -10.250  -0.4044   0.01136   0.00616  -0.1259   0.9839   0.0262
 -10.000  -0.3695   0.01109   0.00586  -0.1278   0.9835   0.0275
  -9.750  -0.3354   0.01060   0.00535  -0.1297   0.9825   0.0295
  -9.500  -0.3038   0.01030   0.00506  -0.1308   0.9804   0.0313
  -9.250  -0.2705   0.01006   0.00479  -0.1323   0.9790   0.0331
  -9.000  -0.2362   0.00968   0.00439  -0.1340   0.9778   0.0355
  -8.750  -0.2022   0.00938   0.00411  -0.1357   0.9766   0.0382
  -8.500  -0.1685   0.00917   0.00388  -0.1372   0.9753   0.0405
  -8.250  -0.1338   0.00883   0.00355  -0.1389   0.9742   0.0451
  -8.000  -0.1001   0.00861   0.00334  -0.1404   0.9728   0.0487
  -7.750  -0.0663   0.00833   0.00310  -0.1419   0.9714   0.0563
  -7.500  -0.0352   0.00809   0.00292  -0.1428   0.9687   0.0672
  -7.250  -0.0040   0.00786   0.00275  -0.1437   0.9657   0.0839
  -7.000   0.0281   0.00760   0.00259  -0.1448   0.9631   0.1070
  -6.750   0.0599   0.00737   0.00244  -0.1459   0.9606   0.1312
  -6.500   0.0925   0.00708   0.00230  -0.1471   0.9583   0.1701
  -6.250   0.1248   0.00674   0.00217  -0.1484   0.9554   0.2283
  -6.000   0.1567   0.00642   0.00207  -0.1496   0.9519   0.2914
  -5.750   0.1886   0.00615   0.00199  -0.1507   0.9486   0.3535
  -5.500   0.2197   0.00597   0.00194  -0.1515   0.9456   0.3976
  -5.250   0.2505   0.00586   0.00192  -0.1521   0.9427   0.4322
  -5.000   0.2803   0.00578   0.00190  -0.1526   0.9389   0.4573
  -4.750   0.3102   0.00570   0.00189  -0.1530   0.9348   0.4827
  -4.500   0.3396   0.00565   0.00186  -0.1532   0.9304   0.5027
  -4.250   0.3690   0.00561   0.00185  -0.1533   0.9253   0.5192
  -4.000   0.3977   0.00554   0.00183  -0.1533   0.9176   0.5376
  -3.750   0.4261   0.00550   0.00180  -0.1532   0.9087   0.5523
  -3.500   0.4542   0.00547   0.00175  -0.1529   0.8973   0.5652
  -3.250   0.4829   0.00545   0.00175  -0.1529   0.8866   0.5783
  -3.000   0.5117   0.00545   0.00175  -0.1529   0.8761   0.5923
  -2.750   0.5402   0.00546   0.00175  -0.1528   0.8633   0.6062
  -2.500   0.5686   0.00548   0.00177  -0.1527   0.8470   0.6176
  -2.250   0.5971   0.00552   0.00178  -0.1526   0.8308   0.6269
  -2.000   0.6250   0.00560   0.00181  -0.1523   0.8082   0.6372
  -1.750   0.6531   0.00569   0.00186  -0.1522   0.7844   0.6472
  -1.500   0.6800   0.00590   0.00193  -0.1517   0.7431   0.6572
  -1.250   0.7036   0.00645   0.00208  -0.1506   0.6435   0.6667
  -1.000   0.7231   0.00768   0.00250  -0.1491   0.4611   0.6756
  -0.750   0.7450   0.00867   0.00289  -0.1481   0.3174   0.6846
  -0.500   0.7690   0.00940   0.00319  -0.1475   0.2192   0.6928
  -0.250   0.7937   0.01000   0.00348  -0.1469   0.1457   0.7008
   0.000   0.8196   0.01046   0.00374  -0.1465   0.1017   0.7081
   0.250   0.8458   0.01082   0.00399  -0.1461   0.0753   0.7154
   0.750   0.8989   0.01147   0.00450  -0.1454   0.0491   0.7289
   1.000   0.9259   0.01172   0.00476  -0.1451   0.0446   0.7353
   1.250   0.9525   0.01202   0.00503  -0.1447   0.0405   0.7410
   1.500   0.9790   0.01230   0.00533  -0.1443   0.0377   0.7467
   1.750   1.0057   0.01255   0.00559  -0.1439   0.0356   0.7526
   2.000   1.0316   0.01291   0.00594  -0.1434   0.0329   0.7579
   2.250   1.0575   0.01323   0.00631  -0.1429   0.0311   0.7634
   2.500   1.0839   0.01350   0.00658  -0.1424   0.0295   0.7693
   2.750   1.1097   0.01381   0.00690  -0.1419   0.0278   0.7745
   3.000   1.1342   0.01430   0.00742  -0.1411   0.0259   0.7798
   3.250   1.1602   0.01458   0.00772  -0.1406   0.0249   0.7850
   3.500   1.1857   0.01490   0.00807  -0.1400   0.0238   0.7895
   3.750   1.2106   0.01527   0.00845  -0.1393   0.0227   0.7940
   4.000   1.2328   0.01603   0.00925  -0.1381   0.0214   0.7987
   4.250   1.2580   0.01636   0.00962  -0.1374   0.0209   0.8034
   4.500   1.2822   0.01676   0.01008  -0.1366   0.0203   0.8081
   4.750   1.3062   0.01720   0.01056  -0.1357   0.0197   0.8136
   5.000   1.3300   0.01763   0.01102  -0.1348   0.0191   0.8188
   5.250   1.3534   0.01807   0.01150  -0.1338   0.0185   0.8234
   5.500   1.3742   0.01886   0.01232  -0.1324   0.0178   0.8282
   5.750   1.3943   0.01979   0.01332  -0.1309   0.0173   0.8326
   6.000   1.4168   0.02028   0.01389  -0.1298   0.0170   0.8365
   6.250   1.4387   0.02084   0.01453  -0.1286   0.0167   0.8407
   6.500   1.4601   0.02147   0.01523  -0.1273   0.0164   0.8453
   6.750   1.4810   0.02211   0.01593  -0.1259   0.0160   0.8495
   7.000   1.5012   0.02276   0.01666  -0.1245   0.0157   0.8541
   7.250   1.5210   0.02344   0.01740  -0.1229   0.0154   0.8593
   7.500   1.5403   0.02411   0.01814  -0.1214   0.0151   0.8640
   7.750   1.5583   0.02487   0.01897  -0.1196   0.0149   0.8686
   8.000   1.5750   0.02575   0.01991  -0.1176   0.0146   0.8737
   8.250   1.5882   0.02699   0.02126  -0.1151   0.0143   0.8786
   8.500   1.5939   0.02923   0.02371  -0.1116   0.0140   0.8838
   8.750   1.6068   0.03016   0.02477  -0.1090   0.0139   0.8895
   9.000   1.6187   0.03098   0.02571  -0.1063   0.0137   0.8957
   9.250   1.6273   0.03181   0.02666  -0.1030   0.0136   0.9033
   9.500   1.6346   0.03289   0.02789  -0.0997   0.0135   0.9132
   9.750   1.6398   0.03407   0.02925  -0.0962   0.0133   0.9327
  10.000   1.6434   0.03534   0.03068  -0.0926   0.0132   1.0001
  10.250   1.6483   0.03688   0.03235  -0.0896   0.0131   1.0001
  10.500   1.6515   0.03857   0.03418  -0.0865   0.0129   1.0001
  10.750   1.6533   0.04042   0.03616  -0.0835   0.0128   1.0001
  11.000   1.6542   0.04236   0.03824  -0.0807   0.0127   1.0001
  11.250   1.6533   0.04452   0.04054  -0.0779   0.0125   1.0001
  11.500   1.6498   0.04705   0.04321  -0.0753   0.0124   1.0001
  11.750   1.6463   0.04960   0.04590  -0.0730   0.0123   1.0001
  12.000   1.6400   0.05262   0.04906  -0.0709   0.0123   1.0001
  12.250   1.6319   0.05598   0.05257  -0.0692   0.0122   1.0001
  12.500   1.6218   0.05973   0.05648  -0.0679   0.0121   1.0001
  12.750   1.6107   0.06389   0.06079  -0.0673   0.0120   1.0001
  13.000   1.5956   0.06891   0.06597  -0.0674   0.0120   1.0001
  13.250   1.5786   0.07466   0.07189  -0.0686   0.0120   1.0001
  13.500   1.5553   0.08218   0.07961  -0.0713   0.0119   1.0001
  13.750   1.5247   0.09214   0.08980  -0.0765   0.0120   1.0001
  14.000   1.4815   0.10622   0.10417  -0.0855   0.0120   1.0001
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