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

NACA 2415 (naca2415-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 2415 (naca2415-il)
Reynolds number: 200,000
Max Cl/Cd: 64.06 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca2415-il-200000.txt
Download as CSV file: xf-naca2415-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2415                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.7945   0.07738   0.07278  -0.0629   1.0000   0.0605
 -14.000  -0.8410   0.06704   0.06224  -0.0702   1.0000   0.0600
 -13.750  -0.8790   0.05958   0.05453  -0.0747   1.0000   0.0598
 -13.500  -0.9100   0.05420   0.04891  -0.0765   1.0000   0.0597
 -13.250  -0.9359   0.05027   0.04473  -0.0758   1.0000   0.0598
 -13.000  -0.9587   0.04737   0.04160  -0.0730   1.0000   0.0599
 -12.750  -0.9793   0.04516   0.03918  -0.0685   1.0000   0.0601
 -12.500  -0.9935   0.04304   0.03679  -0.0644   1.0000   0.0604
 -12.250  -1.0033   0.04117   0.03464  -0.0602   1.0000   0.0607
 -12.000  -0.9989   0.03881   0.03220  -0.0580   1.0000   0.0614
 -11.750  -0.9889   0.03747   0.03087  -0.0559   1.0000   0.0623
 -11.500  -0.9814   0.03633   0.02968  -0.0533   1.0000   0.0632
 -11.250  -0.9739   0.03517   0.02842  -0.0507   1.0000   0.0641
 -11.000  -0.9667   0.03391   0.02703  -0.0479   1.0000   0.0651
 -10.750  -0.9594   0.03260   0.02554  -0.0451   1.0000   0.0660
 -10.500  -0.9512   0.03133   0.02407  -0.0423   1.0000   0.0670
 -10.250  -0.9421   0.03021   0.02272  -0.0396   1.0000   0.0680
 -10.000  -0.9299   0.02883   0.02123  -0.0374   1.0000   0.0692
  -9.750  -0.9147   0.02787   0.02033  -0.0357   1.0000   0.0706
  -9.500  -0.9003   0.02712   0.01955  -0.0337   1.0000   0.0721
  -9.250  -0.8859   0.02634   0.01868  -0.0317   1.0000   0.0738
  -9.000  -0.8710   0.02554   0.01775  -0.0298   1.0000   0.0755
  -8.750  -0.8557   0.02484   0.01687  -0.0278   1.0000   0.0771
  -8.500  -0.8390   0.02379   0.01591  -0.0264   1.0000   0.0793
  -8.250  -0.8220   0.02324   0.01539  -0.0248   1.0000   0.0817
  -8.000  -0.8047   0.02273   0.01480  -0.0233   1.0000   0.0848
  -7.750  -0.7830   0.02197   0.01400  -0.0226   0.9993   0.0882
  -7.500  -0.7448   0.02134   0.01342  -0.0252   0.9954   0.0932
  -7.250  -0.7070   0.02061   0.01266  -0.0276   0.9916   0.0996
  -7.000  -0.6698   0.02012   0.01217  -0.0299   0.9866   0.1074
  -6.750  -0.6306   0.01950   0.01162  -0.0326   0.9827   0.1167
  -6.500  -0.5958   0.01893   0.01108  -0.0344   0.9772   0.1269
  -6.250  -0.5577   0.01845   0.01061  -0.0367   0.9722   0.1390
  -6.000  -0.5160   0.01802   0.01021  -0.0398   0.9690   0.1529
  -5.750  -0.4847   0.01766   0.00985  -0.0407   0.9613   0.1658
  -5.500  -0.4447   0.01722   0.00948  -0.0433   0.9572   0.1818
  -5.250  -0.4085   0.01682   0.00916  -0.0452   0.9517   0.1986
  -5.000  -0.3739   0.01642   0.00885  -0.0467   0.9451   0.2167
  -4.750  -0.3320   0.01599   0.00854  -0.0496   0.9415   0.2385
  -4.500  -0.2964   0.01563   0.00827  -0.0512   0.9355   0.2607
  -4.250  -0.2604   0.01528   0.00796  -0.0528   0.9290   0.2850
  -4.000  -0.2204   0.01479   0.00762  -0.0552   0.9251   0.3108
  -3.750  -0.1895   0.01445   0.00736  -0.0557   0.9172   0.3356
  -3.500  -0.1555   0.01402   0.00703  -0.0567   0.9105   0.3619
  -3.250  -0.1182   0.01354   0.00667  -0.0583   0.9062   0.3915
  -3.000  -0.0936   0.01322   0.00647  -0.0574   0.8948   0.4188
  -2.750  -0.0597   0.01275   0.00614  -0.0582   0.8891   0.4542
  -2.500  -0.0356   0.01244   0.00598  -0.0571   0.8772   0.4905
  -2.250  -0.0065   0.01206   0.00577  -0.0568   0.8688   0.5335
  -2.000   0.0195   0.01177   0.00562  -0.0559   0.8575   0.5772
  -1.750   0.0454   0.01153   0.00551  -0.0550   0.8463   0.6198
  -1.500   0.0734   0.01126   0.00534  -0.0543   0.8366   0.6603
  -1.250   0.0979   0.01111   0.00530  -0.0531   0.8233   0.6982
  -1.000   0.1238   0.01097   0.00525  -0.0520   0.8112   0.7349
  -0.750   0.1508   0.01085   0.00518  -0.0510   0.8000   0.7700
  -0.500   0.1753   0.01082   0.00524  -0.0496   0.7860   0.8030
  -0.250   0.2009   0.01083   0.00529  -0.0483   0.7729   0.8343
   0.000   0.2274   0.01087   0.00530  -0.0472   0.7604   0.8639
   0.250   0.2557   0.01095   0.00535  -0.0464   0.7468   0.8884
   0.500   0.2862   0.01107   0.00544  -0.0462   0.7326   0.9097
   0.750   0.3205   0.01122   0.00552  -0.0469   0.7190   0.9279
   1.000   0.3583   0.01137   0.00557  -0.0484   0.7052   0.9429
   1.250   0.3985   0.01152   0.00561  -0.0505   0.6909   0.9559
   1.500   0.4428   0.01166   0.00566  -0.0536   0.6745   0.9664
   1.750   0.4897   0.01176   0.00566  -0.0574   0.6566   0.9749
   2.000   0.5352   0.01186   0.00566  -0.0609   0.6393   0.9845
   2.250   0.5828   0.01196   0.00569  -0.0650   0.6231   0.9937
   2.500   0.6263   0.01203   0.00568  -0.0685   0.6074   1.0000
   2.750   0.6477   0.01210   0.00567  -0.0675   0.5943   1.0000
   3.250   0.6898   0.01231   0.00575  -0.0652   0.5685   1.0000
   3.500   0.7108   0.01245   0.00585  -0.0639   0.5557   1.0000
   3.750   0.7320   0.01262   0.00592  -0.0627   0.5436   1.0000
   4.000   0.7525   0.01277   0.00602  -0.0613   0.5301   1.0000
   4.250   0.7725   0.01292   0.00615  -0.0598   0.5156   1.0000
   4.500   0.7927   0.01310   0.00628  -0.0583   0.5015   1.0000
   4.750   0.8133   0.01331   0.00641  -0.0569   0.4888   1.0000
   5.000   0.8338   0.01350   0.00657  -0.0555   0.4759   1.0000
   5.250   0.8541   0.01370   0.00676  -0.0540   0.4626   1.0000
   5.500   0.8745   0.01392   0.00695  -0.0525   0.4495   1.0000
   5.750   0.8948   0.01417   0.00713  -0.0510   0.4364   1.0000
   6.000   0.9146   0.01441   0.00734  -0.0494   0.4222   1.0000
   6.250   0.9341   0.01464   0.00756  -0.0478   0.4069   1.0000
   6.500   0.9534   0.01490   0.00779  -0.0462   0.3909   1.0000
   6.750   0.9724   0.01518   0.00804  -0.0445   0.3740   1.0000
   7.000   0.9910   0.01549   0.00830  -0.0428   0.3563   1.0000
   7.250   1.0093   0.01584   0.00859  -0.0411   0.3382   1.0000
   7.500   1.0272   0.01622   0.00892  -0.0393   0.3198   1.0000
   7.750   1.0447   0.01664   0.00928  -0.0376   0.3013   1.0000
   8.000   1.0614   0.01710   0.00967  -0.0357   0.2827   1.0000
   8.250   1.0781   0.01757   0.01011  -0.0339   0.2635   1.0000
   8.500   1.0936   0.01812   0.01060  -0.0319   0.2446   1.0000
   8.750   1.1076   0.01874   0.01115  -0.0298   0.2267   1.0000
   9.000   1.1200   0.01943   0.01176  -0.0274   0.2099   1.0000
   9.250   1.1306   0.02015   0.01243  -0.0248   0.1941   1.0000
   9.500   1.1411   0.02092   0.01315  -0.0222   0.1789   1.0000
   9.750   1.1513   0.02176   0.01394  -0.0198   0.1644   1.0000
  10.000   1.1608   0.02269   0.01482  -0.0174   0.1511   1.0000
  10.250   1.1689   0.02376   0.01582  -0.0150   0.1395   1.0000
  10.500   1.1756   0.02496   0.01695  -0.0127   0.1293   1.0000
  10.750   1.1849   0.02609   0.01810  -0.0107   0.1199   1.0000
  11.000   1.1912   0.02747   0.01945  -0.0086   0.1124   1.0000
  11.250   1.1985   0.02882   0.02079  -0.0067   0.1058   1.0000
  11.500   1.2056   0.03028   0.02226  -0.0050   0.1003   1.0000
  11.750   1.2141   0.03166   0.02368  -0.0035   0.0956   1.0000
  12.000   1.2200   0.03336   0.02529  -0.0018   0.0918   1.0000
  12.250   1.2301   0.03472   0.02678  -0.0006   0.0884   1.0000
  12.500   1.2390   0.03619   0.02828   0.0005   0.0853   1.0000
  12.750   1.2477   0.03778   0.02980   0.0017   0.0826   1.0000
  13.000   1.2574   0.03932   0.03143   0.0028   0.0802   1.0000
  13.250   1.2667   0.04087   0.03309   0.0038   0.0779   1.0000
  13.500   1.2765   0.04241   0.03467   0.0047   0.0760   1.0000
  13.750   1.2872   0.04392   0.03615   0.0055   0.0742   1.0000
  14.000   1.3024   0.04532   0.03751   0.0065   0.0723   1.0000
  14.250   1.3083   0.04721   0.03958   0.0073   0.0710   1.0000
  14.500   1.3149   0.04911   0.04161   0.0080   0.0695   1.0000
  14.750   1.3221   0.05098   0.04358   0.0087   0.0681   1.0000
  15.000   1.3308   0.05276   0.04541   0.0093   0.0669   1.0000
  15.250   1.3426   0.05431   0.04696   0.0099   0.0656   1.0000
  15.500   1.3593   0.05587   0.04850   0.0107   0.0641   1.0000
  15.750   1.3569   0.05859   0.05143   0.0111   0.0634   1.0000
  16.000   1.3552   0.06140   0.05444   0.0113   0.0625   1.0000
  16.250   1.3540   0.06427   0.05749   0.0114   0.0616   1.0000
  16.500   1.3526   0.06724   0.06061   0.0114   0.0607   1.0000
  16.750   1.3506   0.07031   0.06383   0.0111   0.0599   1.0000
  17.000   1.3508   0.07319   0.06681   0.0109   0.0590   1.0000
  17.250   1.3556   0.07559   0.06924   0.0108   0.0581   1.0000
  17.500   1.3721   0.07707   0.07065   0.0117   0.0569   1.0000
  17.750   1.3558   0.08193   0.07576   0.0103   0.0565   1.0000
  18.000   1.3365   0.08746   0.08156   0.0084   0.0562   1.0000
  18.250   1.3152   0.09363   0.08799   0.0058   0.0559   1.0000
  18.500   1.2904   0.10066   0.09529   0.0025   0.0557   1.0000
  18.750   1.2610   0.10888   0.10377  -0.0019   0.0555   1.0000
  19.000   1.2235   0.11911   0.11430  -0.0079   0.0555   1.0000
  19.250   1.1678   0.13376   0.12928  -0.0172   0.0559   1.0000
<< Back to NACA 2415 (naca2415-il)

Polar data table (+)

Polar graphs


<< Back to NACA 2415 (naca2415-il)