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)-0412 AIRFOIL (sc20412-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0412 AIRFOIL (sc20412-il)
Reynolds number: 200,000
Max Cl/Cd: 43 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20412-il-200000-n5.txt
Download as CSV file: xf-sc20412-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0412 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
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.9592   0.07907   0.07413  -0.0382   1.0000   0.0270
 -14.500  -0.9924   0.06977   0.06454  -0.0440   1.0000   0.0270
 -14.250  -1.0140   0.06338   0.05790  -0.0473   1.0000   0.0272
 -14.000  -1.0298   0.05828   0.05257  -0.0493   1.0000   0.0274
 -13.750  -1.0418   0.05397   0.04802  -0.0506   1.0000   0.0277
 -13.500  -1.0509   0.05020   0.04400  -0.0513   1.0000   0.0281
 -13.250  -1.0571   0.04687   0.04041  -0.0515   1.0000   0.0285
 -13.000  -1.0605   0.04392   0.03717  -0.0513   1.0000   0.0289
 -12.750  -1.0558   0.04191   0.03508  -0.0509   1.0000   0.0293
 -12.500  -1.0489   0.04024   0.03336  -0.0504   1.0000   0.0297
 -12.250  -1.0417   0.03865   0.03169  -0.0498   1.0000   0.0301
 -12.000  -1.0343   0.03712   0.03007  -0.0489   1.0000   0.0306
 -11.750  -1.0268   0.03565   0.02849  -0.0479   1.0000   0.0311
 -11.500  -1.0190   0.03423   0.02695  -0.0466   1.0000   0.0317
 -11.250  -1.0083   0.03281   0.02538  -0.0457   1.0000   0.0325
 -11.000  -0.9952   0.03142   0.02379  -0.0449   1.0000   0.0333
 -10.750  -0.9806   0.03018   0.02243  -0.0441   1.0000   0.0341
 -10.500  -0.9648   0.02921   0.02146  -0.0435   1.0000   0.0349
 -10.250  -0.9480   0.02834   0.02054  -0.0429   1.0000   0.0359
 -10.000  -0.9306   0.02745   0.01957  -0.0422   1.0000   0.0371
  -9.750  -0.9126   0.02653   0.01853  -0.0413   1.0000   0.0384
  -9.500  -0.8943   0.02561   0.01750  -0.0404   1.0000   0.0396
  -9.250  -0.8759   0.02477   0.01668  -0.0397   1.0000   0.0406
  -9.000  -0.8564   0.02408   0.01596  -0.0390   1.0000   0.0419
  -8.750  -0.8363   0.02339   0.01522  -0.0383   1.0000   0.0436
  -8.500  -0.8158   0.02273   0.01445  -0.0376   1.0000   0.0454
  -8.250  -0.7958   0.02197   0.01372  -0.0369   1.0000   0.0469
  -8.000  -0.7748   0.02136   0.01310  -0.0363   1.0000   0.0486
  -7.750  -0.7533   0.02079   0.01249  -0.0358   1.0000   0.0508
  -7.500  -0.7313   0.02026   0.01189  -0.0352   1.0000   0.0529
  -7.250  -0.7097   0.01957   0.01124  -0.0348   1.0000   0.0550
  -7.000  -0.6872   0.01904   0.01072  -0.0344   1.0000   0.0575
  -6.750  -0.6641   0.01857   0.01020  -0.0341   1.0000   0.0604
  -6.500  -0.6407   0.01799   0.00966  -0.0339   1.0000   0.0633
  -6.250  -0.6167   0.01753   0.00920  -0.0338   1.0000   0.0665
  -6.000  -0.5922   0.01713   0.00878  -0.0337   1.0000   0.0702
  -5.750  -0.5609   0.01661   0.00832  -0.0352   0.9985   0.0751
  -5.500  -0.5262   0.01620   0.00788  -0.0371   0.9961   0.0811
  -5.250  -0.4910   0.01571   0.00745  -0.0393   0.9940   0.0887
  -5.000  -0.4564   0.01528   0.00705  -0.0412   0.9915   0.0980
  -4.750  -0.4217   0.01484   0.00666  -0.0432   0.9886   0.1106
  -4.500  -0.3857   0.01435   0.00630  -0.0455   0.9860   0.1307
  -4.250  -0.3486   0.01382   0.00595  -0.0482   0.9838   0.1647
  -4.000  -0.3106   0.01320   0.00560  -0.0511   0.9819   0.2203
  -3.750  -0.2731   0.01231   0.00519  -0.0544   0.9792   0.3156
  -3.500  -0.2329   0.01128   0.00494  -0.0582   0.9774   0.4713
  -3.250  -0.1991   0.01124   0.00533  -0.0592   0.9738   0.5689
  -3.000  -0.1629   0.01132   0.00545  -0.0607   0.9710   0.6026
  -2.750  -0.1285   0.01141   0.00552  -0.0620   0.9673   0.6238
  -2.500  -0.0960   0.01153   0.00564  -0.0627   0.9627   0.6384
  -2.250  -0.0619   0.01169   0.00580  -0.0637   0.9593   0.6525
  -2.000  -0.0275   0.01191   0.00605  -0.0646   0.9563   0.6666
  -1.750   0.0027   0.01212   0.00626  -0.0648   0.9500   0.6790
  -1.500   0.0336   0.01234   0.00653  -0.0648   0.9449   0.6870
  -1.250   0.0709   0.01233   0.00648  -0.0667   0.9416   0.6952
  -1.000   0.0985   0.01244   0.00664  -0.0662   0.9339   0.6988
  -0.750   0.1322   0.01242   0.00664  -0.0669   0.9273   0.7026
  -0.500   0.1639   0.01235   0.00657  -0.0674   0.9165   0.7064
  -0.250   0.1984   0.01218   0.00638  -0.0685   0.9042   0.7103
   0.000   0.2316   0.01197   0.00611  -0.0692   0.8835   0.7132
   0.250   0.2607   0.01185   0.00594  -0.0687   0.8591   0.7148
   0.500   0.2886   0.01181   0.00589  -0.0681   0.8372   0.7165
   0.750   0.3168   0.01179   0.00583  -0.0677   0.8129   0.7183
   1.000   0.3449   0.01179   0.00575  -0.0673   0.7809   0.7202
   1.250   0.3729   0.01183   0.00568  -0.0669   0.7428   0.7222
   1.500   0.4003   0.01196   0.00560  -0.0665   0.6890   0.7244
   1.750   0.4251   0.01235   0.00552  -0.0655   0.5813   0.7267
   2.000   0.4469   0.01325   0.00565  -0.0646   0.4295   0.7293
   2.250   0.4713   0.01400   0.00589  -0.0643   0.3262   0.7316
   2.500   0.4954   0.01460   0.00616  -0.0637   0.2497   0.7332
   2.750   0.5204   0.01513   0.00644  -0.0633   0.1947   0.7350
   3.000   0.5463   0.01559   0.00672  -0.0631   0.1598   0.7370
   3.250   0.5732   0.01595   0.00699  -0.0629   0.1386   0.7391
   3.500   0.6005   0.01629   0.00728  -0.0629   0.1221   0.7412
   3.750   0.6281   0.01664   0.00756  -0.0630   0.1094   0.7433
   4.000   0.6558   0.01702   0.00786  -0.0632   0.0994   0.7456
   4.250   0.6843   0.01734   0.00817  -0.0634   0.0914   0.7480
   4.500   0.7109   0.01773   0.00854  -0.0633   0.0849   0.7497
   4.750   0.7370   0.01808   0.00892  -0.0629   0.0794   0.7512
   5.000   0.7624   0.01855   0.00935  -0.0625   0.0747   0.7529
   5.250   0.7886   0.01893   0.00980  -0.0622   0.0705   0.7549
   5.500   0.8143   0.01938   0.01025  -0.0619   0.0667   0.7573
   5.750   0.8402   0.01989   0.01077  -0.0617   0.0634   0.7597
   6.000   0.8667   0.02034   0.01128  -0.0615   0.0601   0.7622
   6.250   0.8929   0.02086   0.01177  -0.0615   0.0572   0.7647
   6.500   0.9181   0.02141   0.01238  -0.0611   0.0545   0.7667
   6.750   0.9425   0.02193   0.01298  -0.0604   0.0520   0.7686
   7.000   0.9666   0.02248   0.01355  -0.0599   0.0497   0.7708
   7.250   0.9906   0.02313   0.01426  -0.0593   0.0476   0.7731
   7.500   1.0151   0.02374   0.01497  -0.0588   0.0453   0.7754
   7.750   1.0395   0.02437   0.01564  -0.0584   0.0436   0.7779
   8.000   1.0630   0.02515   0.01638  -0.0580   0.0421   0.7805
   8.250   1.0872   0.02589   0.01729  -0.0575   0.0403   0.7829
   8.500   1.1095   0.02659   0.01811  -0.0566   0.0386   0.7850
   8.750   1.1314   0.02728   0.01886  -0.0558   0.0373   0.7873
   9.000   1.1525   0.02814   0.01974  -0.0549   0.0364   0.7898
   9.250   1.1739   0.02917   0.02098  -0.0540   0.0352   0.7925
   9.500   1.1950   0.03024   0.02221  -0.0532   0.0341   0.7952
   9.750   1.2157   0.03125   0.02334  -0.0524   0.0331   0.7980
  10.000   1.2349   0.03215   0.02433  -0.0513   0.0323   0.8003
  10.250   1.2529   0.03305   0.02530  -0.0501   0.0316   0.8026
  10.500   1.2694   0.03427   0.02665  -0.0487   0.0308   0.8052
  10.750   1.2846   0.03573   0.02840  -0.0472   0.0300   0.8081
  11.000   1.2985   0.03721   0.03009  -0.0457   0.0292   0.8112
  11.250   1.3111   0.03872   0.03178  -0.0440   0.0286   0.8146
  11.500   1.3210   0.04017   0.03342  -0.0420   0.0281   0.8174
  11.750   1.3279   0.04160   0.03502  -0.0396   0.0277   0.8205
  12.000   1.3310   0.04301   0.03656  -0.0368   0.0274   0.8240
  12.250   1.3350   0.04463   0.03830  -0.0345   0.0271   0.8277
  12.750   1.3372   0.04868   0.04260  -0.0304   0.0266   0.8342
  13.000   1.3277   0.05190   0.04617  -0.0283   0.0264   0.8374
  13.250   1.3148   0.05570   0.05030  -0.0269   0.0262   0.8408
  13.500   1.2979   0.06029   0.05521  -0.0266   0.0260   0.8444
  13.750   1.2767   0.06589   0.06112  -0.0275   0.0259   0.8476
  14.000   1.2501   0.07285   0.06840  -0.0301   0.0259   0.8502
  14.250   1.2160   0.08230   0.07817  -0.0357   0.0259   0.8526
  14.500   1.1660   0.09743   0.09366  -0.0467   0.0261   0.8539
<< Back to NASA SC(2)-0412 AIRFOIL (sc20412-il)

Polar data table (+)

Polar graphs


<< Back to NASA SC(2)-0412 AIRFOIL (sc20412-il)