Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NASA SC(2)-0414 AIRFOIL (sc20414-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0414 AIRFOIL (sc20414-il)
Reynolds number: 200,000
Max Cl/Cd: 43.33 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20414-il-200000-n5.txt
Download as CSV file: xf-sc20414-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0414 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.750  -0.9831   0.09737   0.09210  -0.0367   1.0000   0.0343
 -16.500  -1.0212   0.08626   0.08067  -0.0436   1.0000   0.0344
 -16.250  -1.0457   0.07838   0.07253  -0.0481   1.0000   0.0346
 -16.000  -1.0639   0.07208   0.06597  -0.0513   1.0000   0.0348
 -15.750  -1.0779   0.06678   0.06042  -0.0537   1.0000   0.0350
 -15.500  -1.0841   0.06285   0.05633  -0.0550   1.0000   0.0353
 -15.250  -1.0832   0.06003   0.05345  -0.0557   1.0000   0.0356
 -15.000  -1.0820   0.05737   0.05071  -0.0563   1.0000   0.0359
 -14.750  -1.0804   0.05484   0.04811  -0.0567   1.0000   0.0363
 -14.500  -1.0783   0.05243   0.04560  -0.0571   1.0000   0.0367
 -14.250  -1.0755   0.05012   0.04319  -0.0573   1.0000   0.0372
 -14.000  -1.0722   0.04791   0.04086  -0.0573   1.0000   0.0378
 -13.750  -1.0680   0.04579   0.03861  -0.0572   1.0000   0.0385
 -13.500  -1.0629   0.04378   0.03644  -0.0569   1.0000   0.0391
 -13.250  -1.0568   0.04187   0.03434  -0.0565   1.0000   0.0398
 -13.000  -1.0482   0.04023   0.03259  -0.0560   1.0000   0.0404
 -12.750  -1.0380   0.03883   0.03118  -0.0554   1.0000   0.0410
 -12.500  -1.0274   0.03751   0.02983  -0.0549   1.0000   0.0416
 -12.250  -1.0165   0.03624   0.02851  -0.0542   1.0000   0.0423
 -12.000  -1.0052   0.03502   0.02721  -0.0534   1.0000   0.0431
 -11.750  -0.9934   0.03385   0.02596  -0.0525   1.0000   0.0440
 -11.500  -0.9815   0.03275   0.02474  -0.0515   1.0000   0.0451
 -11.250  -0.9696   0.03170   0.02363  -0.0503   1.0000   0.0461
 -11.000  -0.9590   0.03074   0.02269  -0.0490   1.0000   0.0469
 -10.750  -0.9492   0.02988   0.02181  -0.0473   1.0000   0.0478
 -10.500  -0.9409   0.02907   0.02098  -0.0453   1.0000   0.0489
 -10.250  -0.9331   0.02829   0.02016  -0.0430   1.0000   0.0499
 -10.000  -0.9219   0.02751   0.01931  -0.0412   1.0000   0.0511
  -9.750  -0.9105   0.02672   0.01848  -0.0394   1.0000   0.0522
  -9.500  -0.8991   0.02595   0.01774  -0.0379   1.0000   0.0534
  -9.250  -0.8861   0.02526   0.01705  -0.0364   1.0000   0.0548
  -9.000  -0.8720   0.02461   0.01636  -0.0351   1.0000   0.0565
  -8.750  -0.8567   0.02398   0.01566  -0.0338   1.0000   0.0582
  -8.500  -0.8415   0.02327   0.01497  -0.0327   1.0000   0.0598
  -8.250  -0.8250   0.02264   0.01435  -0.0318   1.0000   0.0615
  -8.000  -0.8058   0.02207   0.01377  -0.0312   0.9998   0.0636
  -7.750  -0.7729   0.02146   0.01310  -0.0330   0.9970   0.0665
  -7.500  -0.7398   0.02075   0.01244  -0.0352   0.9942   0.0696
  -7.250  -0.7066   0.02019   0.01186  -0.0371   0.9914   0.0732
  -7.000  -0.6744   0.01957   0.01125  -0.0389   0.9880   0.0770
  -6.750  -0.6409   0.01902   0.01072  -0.0409   0.9849   0.0815
  -6.500  -0.6065   0.01848   0.01019  -0.0430   0.9824   0.0865
  -6.250  -0.5721   0.01796   0.00970  -0.0451   0.9798   0.0926
  -6.000  -0.5400   0.01744   0.00921  -0.0467   0.9755   0.0990
  -5.750  -0.5054   0.01697   0.00875  -0.0488   0.9722   0.1075
  -5.500  -0.4692   0.01643   0.00830  -0.0512   0.9697   0.1183
  -5.250  -0.4319   0.01593   0.00787  -0.0538   0.9678   0.1333
  -5.000  -0.4002   0.01544   0.00747  -0.0553   0.9627   0.1506
  -4.750  -0.3645   0.01486   0.00706  -0.0578   0.9595   0.1788
  -4.500  -0.3267   0.01417   0.00662  -0.0608   0.9572   0.2235
  -4.000  -0.2438   0.01218   0.00565  -0.0693   0.9539   0.4193
  -3.750  -0.2120   0.01192   0.00593  -0.0702   0.9489   0.5233
  -3.500  -0.1797   0.01201   0.00613  -0.0708   0.9445   0.5643
  -3.250  -0.1450   0.01208   0.00620  -0.0720   0.9411   0.5870
  -3.000  -0.1092   0.01215   0.00626  -0.0734   0.9384   0.6045
  -2.750  -0.0805   0.01230   0.00642  -0.0733   0.9316   0.6172
  -2.500  -0.0466   0.01237   0.00645  -0.0743   0.9273   0.6290
  -2.250  -0.0146   0.01256   0.00666  -0.0747   0.9236   0.6378
  -2.000   0.0156   0.01275   0.00685  -0.0748   0.9178   0.6485
  -1.750   0.0439   0.01307   0.00720  -0.0742   0.9119   0.6583
  -1.500   0.0751   0.01325   0.00738  -0.0745   0.9076   0.6660
  -1.250   0.1027   0.01343   0.00761  -0.0738   0.9011   0.6701
  -1.000   0.1321   0.01349   0.00766  -0.0737   0.8931   0.6747
  -0.750   0.1668   0.01332   0.00744  -0.0751   0.8851   0.6799
  -0.500   0.1972   0.01319   0.00728  -0.0752   0.8725   0.6826
  -0.250   0.2249   0.01312   0.00720  -0.0746   0.8561   0.6842
   0.000   0.2527   0.01304   0.00707  -0.0738   0.8351   0.6862
   0.250   0.2803   0.01300   0.00696  -0.0731   0.8114   0.6884
   0.500   0.3093   0.01295   0.00687  -0.0730   0.7908   0.6905
   0.750   0.3390   0.01291   0.00678  -0.0731   0.7712   0.6927
   1.000   0.3692   0.01287   0.00667  -0.0734   0.7485   0.6953
   1.250   0.4003   0.01284   0.00653  -0.0740   0.7214   0.6985
   1.500   0.4297   0.01287   0.00644  -0.0741   0.6828   0.7008
   1.750   0.4551   0.01307   0.00641  -0.0732   0.6213   0.7021
   2.000   0.4761   0.01368   0.00646  -0.0716   0.5053   0.7035
   2.250   0.4965   0.01450   0.00672  -0.0702   0.3921   0.7050
   2.500   0.5194   0.01519   0.00700  -0.0695   0.3108   0.7066
   2.750   0.5440   0.01576   0.00727  -0.0692   0.2483   0.7084
   3.000   0.5698   0.01625   0.00752  -0.0690   0.2042   0.7104
   3.500   0.6243   0.01703   0.00801  -0.0692   0.1526   0.7155
   3.750   0.6530   0.01736   0.00825  -0.0696   0.1361   0.7182
   4.000   0.6799   0.01772   0.00853  -0.0695   0.1241   0.7201
   4.250   0.7053   0.01807   0.00886  -0.0691   0.1146   0.7217
   4.500   0.7310   0.01841   0.00921  -0.0686   0.1068   0.7233
   4.750   0.7565   0.01881   0.00957  -0.0682   0.1000   0.7250
   5.000   0.7828   0.01916   0.00994  -0.0680   0.0942   0.7268
   5.250   0.8085   0.01958   0.01032  -0.0677   0.0891   0.7287
   5.500   0.8348   0.01998   0.01073  -0.0675   0.0846   0.7307
   5.750   0.8610   0.02040   0.01115  -0.0674   0.0804   0.7330
   6.000   0.8870   0.02089   0.01161  -0.0672   0.0767   0.7354
   6.250   0.9142   0.02132   0.01206  -0.0673   0.0731   0.7381
   6.500   0.9377   0.02179   0.01255  -0.0666   0.0701   0.7396
   6.750   0.9614   0.02230   0.01310  -0.0658   0.0674   0.7413
   7.000   0.9854   0.02278   0.01364  -0.0652   0.0647   0.7430
   7.250   1.0092   0.02329   0.01416  -0.0646   0.0624   0.7449
   7.500   1.0326   0.02388   0.01478  -0.0640   0.0603   0.7469
   7.750   1.0567   0.02443   0.01540  -0.0634   0.0580   0.7491
   8.000   1.0805   0.02499   0.01599  -0.0629   0.0561   0.7515
   8.250   1.1036   0.02564   0.01663  -0.0624   0.0545   0.7539
   8.500   1.1267   0.02636   0.01741  -0.0618   0.0529   0.7562
   8.750   1.1478   0.02703   0.01818  -0.0608   0.0513   0.7579
   9.000   1.1684   0.02769   0.01891  -0.0597   0.0498   0.7599
   9.250   1.1884   0.02838   0.01964  -0.0586   0.0485   0.7621
   9.500   1.2078   0.02921   0.02051  -0.0575   0.0474   0.7644
   9.750   1.2280   0.03004   0.02149  -0.0564   0.0461   0.7668
  10.000   1.2475   0.03092   0.02247  -0.0554   0.0449   0.7693
  10.250   1.2663   0.03181   0.02342  -0.0543   0.0439   0.7718
  10.500   1.2834   0.03267   0.02434  -0.0530   0.0431   0.7739
  10.750   1.2980   0.03360   0.02531  -0.0513   0.0423   0.7758
  11.000   1.3104   0.03465   0.02650  -0.0492   0.0415   0.7778
  11.250   1.3216   0.03574   0.02779  -0.0470   0.0406   0.7801
  11.500   1.3335   0.03691   0.02910  -0.0451   0.0398   0.7826
  11.750   1.3449   0.03811   0.03043  -0.0433   0.0390   0.7853
  12.000   1.3559   0.03937   0.03179  -0.0417   0.0384   0.7883
  12.250   1.3656   0.04069   0.03320  -0.0400   0.0379   0.7910
  12.500   1.3737   0.04207   0.03467  -0.0381   0.0374   0.7932
  12.750   1.3811   0.04363   0.03629  -0.0365   0.0370   0.7957
  13.000   1.3854   0.04558   0.03844  -0.0347   0.0366   0.7983
  13.250   1.3873   0.04781   0.04093  -0.0331   0.0361   0.8012
  13.500   1.3876   0.05026   0.04361  -0.0316   0.0356   0.8041
  13.750   1.3864   0.05294   0.04650  -0.0306   0.0351   0.8070
  14.000   1.3829   0.05578   0.04956  -0.0295   0.0347   0.8090
  14.250   1.3781   0.05888   0.05286  -0.0289   0.0343   0.8111
  14.500   1.3720   0.06229   0.05647  -0.0288   0.0340   0.8133
  14.750   1.3649   0.06600   0.06035  -0.0291   0.0337   0.8157
  15.000   1.3565   0.07010   0.06462  -0.0299   0.0334   0.8181
  15.250   1.3459   0.07475   0.06944  -0.0314   0.0332   0.8205
  15.500   1.3327   0.08014   0.07500  -0.0336   0.0330   0.8227
  15.750   1.3179   0.08613   0.08117  -0.0366   0.0328   0.8246
  16.000   1.2954   0.09398   0.08925  -0.0410   0.0327   0.8260
  16.250   1.2580   0.10573   0.10132  -0.0488   0.0327   0.8268
<< Back to NASA SC(2)-0414 AIRFOIL (sc20414-il)

Polar data table (+)

Polar graphs


<< Back to NASA SC(2)-0414 AIRFOIL (sc20414-il)