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NASA SC(2)-0410 AIRFOIL (sc20410-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0410 AIRFOIL (sc20410-il)
Reynolds number: 500,000
Max Cl/Cd: 60.53 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20410-il-500000-n5.txt
Download as CSV file: xf-sc20410-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -1.0901   0.07627   0.07288  -0.0255   1.0000   0.0128
 -15.250  -1.1174   0.06653   0.06291  -0.0322   1.0000   0.0128
 -15.000  -1.1357   0.05965   0.05583  -0.0365   1.0000   0.0128
 -14.750  -1.1485   0.05434   0.05036  -0.0393   1.0000   0.0129
 -14.500  -1.1576   0.04997   0.04583  -0.0412   1.0000   0.0129
 -14.250  -1.1632   0.04633   0.04203  -0.0424   1.0000   0.0130
 -14.000  -1.1662   0.04317   0.03874  -0.0431   1.0000   0.0130
 -13.750  -1.1669   0.04040   0.03583  -0.0435   1.0000   0.0131
 -13.500  -1.1654   0.03797   0.03327  -0.0436   1.0000   0.0132
 -13.250  -1.1622   0.03578   0.03095  -0.0434   1.0000   0.0133
 -13.000  -1.1575   0.03384   0.02888  -0.0430   1.0000   0.0135
 -12.750  -1.1518   0.03208   0.02698  -0.0424   1.0000   0.0136
 -12.500  -1.1457   0.03049   0.02528  -0.0415   1.0000   0.0137
 -12.250  -1.1354   0.02901   0.02367  -0.0410   1.0000   0.0139
 -12.000  -1.1213   0.02760   0.02213  -0.0410   1.0000   0.0141
 -11.750  -1.1052   0.02631   0.02071  -0.0409   1.0000   0.0143
 -11.500  -1.0876   0.02514   0.01942  -0.0407   1.0000   0.0145
 -11.250  -1.0690   0.02407   0.01822  -0.0405   1.0000   0.0147
 -11.000  -1.0492   0.02307   0.01711  -0.0402   1.0000   0.0149
 -10.750  -1.0286   0.02215   0.01608  -0.0400   1.0000   0.0152
 -10.500  -1.0070   0.02133   0.01515  -0.0398   1.0000   0.0154
 -10.250  -0.9860   0.02031   0.01409  -0.0397   1.0000   0.0158
 -10.000  -0.9635   0.01955   0.01327  -0.0396   1.0000   0.0163
  -9.750  -0.9402   0.01888   0.01255  -0.0394   1.0000   0.0167
  -9.500  -0.9165   0.01823   0.01185  -0.0393   1.0000   0.0171
  -9.250  -0.8924   0.01760   0.01116  -0.0392   1.0000   0.0176
  -9.000  -0.8680   0.01700   0.01050  -0.0392   1.0000   0.0181
  -8.750  -0.8431   0.01643   0.00987  -0.0392   1.0000   0.0187
  -8.500  -0.8180   0.01587   0.00925  -0.0392   1.0000   0.0192
  -8.250  -0.7926   0.01532   0.00869  -0.0392   1.0000   0.0201
  -8.000  -0.7668   0.01486   0.00822  -0.0393   1.0000   0.0211
  -7.750  -0.7409   0.01443   0.00776  -0.0393   1.0000   0.0223
  -7.500  -0.7148   0.01401   0.00731  -0.0393   1.0000   0.0236
  -7.250  -0.6886   0.01362   0.00692  -0.0394   1.0000   0.0254
  -7.000  -0.6624   0.01329   0.00658  -0.0394   1.0000   0.0276
  -6.750  -0.6360   0.01294   0.00623  -0.0395   1.0000   0.0299
  -6.500  -0.6096   0.01264   0.00593  -0.0395   1.0000   0.0324
  -6.250  -0.5832   0.01239   0.00565  -0.0395   1.0000   0.0344
  -6.000  -0.5565   0.01206   0.00536  -0.0396   1.0000   0.0371
  -5.750  -0.5290   0.01181   0.00511  -0.0398   0.9998   0.0397
  -5.500  -0.4956   0.01154   0.00482  -0.0412   0.9985   0.0424
  -5.250  -0.4622   0.01124   0.00456  -0.0427   0.9971   0.0463
  -5.000  -0.4285   0.01103   0.00434  -0.0442   0.9955   0.0502
  -4.750  -0.3938   0.01072   0.00409  -0.0460   0.9942   0.0566
  -4.500  -0.3601   0.01047   0.00385  -0.0475   0.9918   0.0623
  -4.250  -0.3259   0.01019   0.00362  -0.0490   0.9894   0.0697
  -4.000  -0.2917   0.00994   0.00341  -0.0506   0.9873   0.0791
  -3.750  -0.2571   0.00967   0.00321  -0.0523   0.9856   0.0937
  -3.500  -0.2218   0.00934   0.00301  -0.0542   0.9841   0.1198
  -3.250  -0.1871   0.00895   0.00282  -0.0561   0.9819   0.1634
  -3.000  -0.1525   0.00851   0.00262  -0.0580   0.9790   0.2239
  -2.750  -0.1161   0.00792   0.00240  -0.0605   0.9767   0.3162
  -2.500  -0.0782   0.00718   0.00214  -0.0635   0.9748   0.4407
  -2.250  -0.0408   0.00662   0.00213  -0.0660   0.9729   0.5842
  -2.000  -0.0069   0.00656   0.00214  -0.0672   0.9675   0.6161
  -1.750   0.0275   0.00652   0.00213  -0.0684   0.9604   0.6336
  -1.500   0.0609   0.00652   0.00216  -0.0694   0.9504   0.6535
  -1.250   0.0933   0.00654   0.00218  -0.0700   0.9351   0.6666
  -1.000   0.1239   0.00656   0.00217  -0.0702   0.9155   0.6749
  -0.750   0.1520   0.00661   0.00218  -0.0699   0.8907   0.6800
  -0.500   0.1800   0.00671   0.00217  -0.0695   0.8646   0.6862
  -0.250   0.2068   0.00684   0.00219  -0.0689   0.8292   0.6916
   0.000   0.2333   0.00703   0.00222  -0.0683   0.7824   0.6961
   0.250   0.2600   0.00727   0.00223  -0.0677   0.7225   0.6993
   0.500   0.2863   0.00765   0.00225  -0.0673   0.6402   0.7018
   0.750   0.3113   0.00834   0.00235  -0.0668   0.5003   0.7038
   1.000   0.3369   0.00906   0.00253  -0.0667   0.3682   0.7056
   1.250   0.3639   0.00952   0.00268  -0.0666   0.2855   0.7073
   1.750   0.4186   0.01032   0.00299  -0.0667   0.1632   0.7106
   2.000   0.4464   0.01062   0.00315  -0.0667   0.1279   0.7125
   2.250   0.4745   0.01088   0.00331  -0.0668   0.1060   0.7144
   2.500   0.5027   0.01112   0.00347  -0.0669   0.0878   0.7161
   2.750   0.5310   0.01135   0.00365  -0.0670   0.0760   0.7179
   3.000   0.5591   0.01159   0.00384  -0.0670   0.0667   0.7196
   3.250   0.5874   0.01181   0.00404  -0.0671   0.0609   0.7213
   3.500   0.6153   0.01205   0.00425  -0.0671   0.0548   0.7229
   3.750   0.6431   0.01226   0.00447  -0.0671   0.0501   0.7244
   4.000   0.6707   0.01253   0.00472  -0.0670   0.0461   0.7261
   4.250   0.6985   0.01275   0.00498  -0.0669   0.0434   0.7281
   4.500   0.7261   0.01300   0.00522  -0.0669   0.0401   0.7302
   4.750   0.7536   0.01329   0.00551  -0.0668   0.0373   0.7323
   5.000   0.7812   0.01354   0.00579  -0.0668   0.0346   0.7343
   5.250   0.8084   0.01386   0.00609  -0.0667   0.0321   0.7363
   5.500   0.8358   0.01416   0.00642  -0.0666   0.0300   0.7383
   5.750   0.8628   0.01447   0.00676  -0.0664   0.0277   0.7401
   6.000   0.8893   0.01484   0.00715  -0.0662   0.0257   0.7420
   6.250   0.9160   0.01519   0.00755  -0.0659   0.0241   0.7440
   6.500   0.9424   0.01557   0.00797  -0.0657   0.0226   0.7461
   6.750   0.9684   0.01603   0.00844  -0.0654   0.0212   0.7484
   7.000   0.9946   0.01645   0.00892  -0.0651   0.0203   0.7508
   7.250   1.0206   0.01689   0.00941  -0.0648   0.0193   0.7533
   7.500   1.0463   0.01737   0.00992  -0.0645   0.0185   0.7556
   7.750   1.0714   0.01790   0.01051  -0.0640   0.0179   0.7577
   8.000   1.0956   0.01855   0.01122  -0.0635   0.0173   0.7600
   8.250   1.1202   0.01914   0.01190  -0.0630   0.0170   0.7628
   8.500   1.1445   0.01976   0.01263  -0.0624   0.0166   0.7658
   8.750   1.1685   0.02043   0.01339  -0.0618   0.0163   0.7688
   9.000   1.1921   0.02113   0.01417  -0.0612   0.0159   0.7717
   9.250   1.2151   0.02184   0.01499  -0.0605   0.0156   0.7742
   9.500   1.2377   0.02259   0.01586  -0.0598   0.0153   0.7770
   9.750   1.2599   0.02337   0.01674  -0.0590   0.0150   0.7800
  10.000   1.2815   0.02421   0.01767  -0.0581   0.0148   0.7832
  10.250   1.3024   0.02512   0.01868  -0.0572   0.0145   0.7865
  10.500   1.3216   0.02617   0.01985  -0.0561   0.0142   0.7893
  10.750   1.3384   0.02751   0.02132  -0.0547   0.0139   0.7925
  11.000   1.3571   0.02854   0.02252  -0.0535   0.0138   0.7960
  11.250   1.3745   0.02968   0.02383  -0.0522   0.0136   0.7997
  11.500   1.3900   0.03097   0.02530  -0.0507   0.0134   0.8033
  11.750   1.4037   0.03236   0.02689  -0.0490   0.0133   0.8070
  12.000   1.4153   0.03386   0.02861  -0.0471   0.0131   0.8111
  12.250   1.4246   0.03549   0.03043  -0.0450   0.0130   0.8154
  12.500   1.4307   0.03721   0.03236  -0.0426   0.0128   0.8192
  12.750   1.4303   0.03900   0.03434  -0.0393   0.0127   0.8235
  13.000   1.4264   0.04099   0.03653  -0.0359   0.0127   0.8283
  13.250   1.4208   0.04337   0.03912  -0.0331   0.0126   0.8329
  13.500   1.4129   0.04616   0.04212  -0.0309   0.0125   0.8376
  13.750   1.4020   0.04960   0.04577  -0.0296   0.0124   0.8426
  14.000   1.3880   0.05386   0.05026  -0.0295   0.0124   0.8474
  14.250   1.3688   0.05948   0.05612  -0.0310   0.0124   0.8521
  14.500   1.3429   0.06744   0.06435  -0.0355   0.0124   0.8568
  14.750   1.2962   0.08272   0.07998  -0.0472   0.0125   0.8597
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