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

NACA 24112 (naca24112-jf) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 24112 (naca24112-jf)
Reynolds number: 50,000
Max Cl/Cd: 27.59 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca24112-jf-50000-n5.txt
Download as CSV file: xf-naca24112-jf-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 24112                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5414   0.09724   0.09004  -0.0115   1.0000   0.0698
  -9.500  -0.5459   0.09164   0.08448  -0.0153   1.0000   0.0686
  -9.250  -0.5564   0.08593   0.07878  -0.0190   1.0000   0.0673
  -9.000  -0.5714   0.08078   0.07361  -0.0210   1.0000   0.0661
  -8.750  -0.5868   0.07581   0.06855  -0.0219   1.0000   0.0651
  -8.500  -0.5987   0.07087   0.06343  -0.0222   1.0000   0.0641
  -8.250  -0.6063   0.06623   0.05854  -0.0217   1.0000   0.0635
  -8.000  -0.6044   0.06266   0.05480  -0.0208   1.0000   0.0640
  -7.750  -0.5990   0.05954   0.05151  -0.0198   1.0000   0.0651
  -7.500  -0.5929   0.05640   0.04816  -0.0185   1.0000   0.0663
  -7.250  -0.5859   0.05320   0.04468  -0.0170   1.0000   0.0674
  -7.000  -0.5774   0.05002   0.04116  -0.0154   1.0000   0.0682
  -6.750  -0.5670   0.04695   0.03773  -0.0136   1.0000   0.0687
  -6.500  -0.5550   0.04413   0.03451  -0.0117   1.0000   0.0699
  -6.250  -0.5420   0.04155   0.03140  -0.0095   1.0000   0.0720
  -6.000  -0.5258   0.03940   0.02909  -0.0081   1.0000   0.0740
  -5.750  -0.5079   0.03757   0.02716  -0.0067   1.0000   0.0759
  -5.500  -0.4895   0.03575   0.02513  -0.0051   1.0000   0.0779
  -5.250  -0.4706   0.03414   0.02325  -0.0036   1.0000   0.0813
  -5.000  -0.4507   0.03258   0.02128  -0.0020   1.0000   0.0846
  -4.750  -0.4300   0.03105   0.01974  -0.0009   1.0000   0.0872
  -4.500  -0.4096   0.02992   0.01860   0.0003   1.0000   0.0913
  -4.250  -0.3885   0.02888   0.01739   0.0016   1.0000   0.0963
  -4.000  -0.3664   0.02779   0.01624   0.0027   1.0000   0.1004
  -3.750  -0.3461   0.02699   0.01551   0.0038   1.0000   0.1061
  -3.500  -0.3101   0.02612   0.01449   0.0023   0.9929   0.1143
  -3.250  -0.2606   0.02506   0.01347  -0.0019   0.9761   0.1270
  -3.000  -0.2129   0.02404   0.01245  -0.0058   0.9581   0.1425
  -2.750  -0.1689   0.02303   0.01149  -0.0090   0.9379   0.1639
  -2.500  -0.1324   0.02195   0.01061  -0.0109   0.9139   0.1973
  -2.250  -0.1141   0.01918   0.01003  -0.0094   0.8916   0.5426
  -2.000  -0.0387   0.01968   0.01123  -0.0120   0.8740   0.8900
  -1.750   0.0597   0.02024   0.01132  -0.0225   0.8460   0.9614
  -1.500   0.1478   0.01995   0.01058  -0.0333   0.8079   1.0000
  -1.250   0.1685   0.01985   0.01021  -0.0318   0.7723   1.0000
  -1.000   0.1888   0.01980   0.00988  -0.0303   0.7398   1.0000
  -0.750   0.2093   0.01979   0.00962  -0.0289   0.7101   1.0000
  -0.500   0.2302   0.01981   0.00939  -0.0276   0.6834   1.0000
  -0.250   0.2516   0.01987   0.00921  -0.0264   0.6583   1.0000
   0.000   0.2732   0.01995   0.00906  -0.0252   0.6365   1.0000
   0.250   0.2951   0.02007   0.00899  -0.0242   0.6149   1.0000
   0.500   0.3171   0.02021   0.00896  -0.0233   0.5954   1.0000
   0.750   0.3393   0.02038   0.00896  -0.0223   0.5778   1.0000
   1.000   0.3616   0.02057   0.00900  -0.0214   0.5614   1.0000
   1.250   0.3840   0.02078   0.00908  -0.0205   0.5462   1.0000
   1.500   0.4066   0.02101   0.00918  -0.0196   0.5325   1.0000
   1.750   0.4291   0.02126   0.00930  -0.0187   0.5196   1.0000
   2.000   0.4519   0.02155   0.00953  -0.0179   0.5064   1.0000
   2.250   0.4749   0.02186   0.00978  -0.0172   0.4947   1.0000
   2.500   0.4979   0.02217   0.00998  -0.0163   0.4844   1.0000
   2.750   0.5205   0.02252   0.01031  -0.0155   0.4731   1.0000
   3.000   0.5432   0.02291   0.01067  -0.0147   0.4631   1.0000
   3.250   0.5659   0.02328   0.01097  -0.0138   0.4540   1.0000
   3.500   0.5881   0.02372   0.01144  -0.0130   0.4440   1.0000
   3.750   0.6110   0.02411   0.01175  -0.0121   0.4361   1.0000
   4.000   0.6328   0.02464   0.01236  -0.0113   0.4264   1.0000
   4.250   0.6556   0.02506   0.01270  -0.0104   0.4190   1.0000
   4.500   0.6768   0.02565   0.01340  -0.0095   0.4097   1.0000
   4.750   0.6998   0.02610   0.01378  -0.0086   0.4029   1.0000
   5.000   0.7203   0.02678   0.01461  -0.0077   0.3938   1.0000
   5.250   0.7431   0.02724   0.01502  -0.0068   0.3870   1.0000
   5.500   0.7630   0.02801   0.01598  -0.0058   0.3785   1.0000
   5.750   0.7854   0.02853   0.01648  -0.0049   0.3716   1.0000
   6.000   0.8048   0.02934   0.01744  -0.0039   0.3634   1.0000
   6.250   0.8264   0.02995   0.01810  -0.0029   0.3565   1.0000
   6.500   0.8459   0.03077   0.01905  -0.0019   0.3489   1.0000
   6.750   0.8662   0.03149   0.01986  -0.0009   0.3414   1.0000
   7.000   0.8865   0.03226   0.02071   0.0001   0.3346   1.0000
   7.250   0.9045   0.03318   0.02182   0.0012   0.3266   1.0000
   7.500   0.9266   0.03377   0.02242   0.0022   0.3202   1.0000
   7.750   0.9413   0.03499   0.02390   0.0034   0.3118   1.0000
   8.000   0.9653   0.03536   0.02425   0.0043   0.3056   1.0000
   8.250   0.9762   0.03689   0.02612   0.0057   0.2968   1.0000
   8.500   0.9997   0.03725   0.02646   0.0066   0.2903   1.0000
   8.750   1.0086   0.03888   0.02842   0.0081   0.2815   1.0000
   9.000   1.0320   0.03917   0.02871   0.0090   0.2748   1.0000
   9.250   1.0377   0.04100   0.03087   0.0107   0.2659   1.0000
   9.500   1.0624   0.04105   0.03089   0.0116   0.2590   1.0000
   9.750   1.0625   0.04325   0.03344   0.0135   0.2501   1.0000
  10.000   1.0863   0.04323   0.03340   0.0145   0.2429   1.0000
  10.250   1.0815   0.04569   0.03619   0.0165   0.2343   1.0000
  10.500   1.0986   0.04609   0.03663   0.0179   0.2266   1.0000
  10.750   1.0917   0.04855   0.03934   0.0198   0.2188   1.0000
  11.000   1.1015   0.04940   0.04025   0.0213   0.2113   1.0000
  11.250   1.0775   0.05316   0.04421   0.0234   0.2054   1.0000
  11.500   1.0936   0.05332   0.04439   0.0247   0.1978   1.0000
  11.750   1.0298   0.06312   0.05442   0.0223   0.1942   1.0000
  12.000   1.0799   0.05882   0.05006   0.0255   0.1848   1.0000
  12.250   0.8937   0.09266   0.08391   0.0073   0.1790   1.0000
  12.500   0.9164   0.09146   0.08283   0.0090   0.1733   1.0000
<< Back to NACA 24112 (naca24112-jf)

Polar data table (+)

Polar graphs


<< Back to NACA 24112 (naca24112-jf)