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NACA 2410 (naca2410-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 2410 (naca2410-il)
Reynolds number: 200,000
Max Cl/Cd: 61.97 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca2410-il-200000-n5.txt
Download as CSV file: xf-naca2410-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2410                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.5726   0.10935   0.10553  -0.0131   1.0000   0.0206
 -11.250  -0.8170   0.04734   0.04308  -0.0569   1.0000   0.0184
 -11.000  -0.8291   0.04366   0.03921  -0.0569   1.0000   0.0186
 -10.750  -0.8248   0.04161   0.03707  -0.0564   1.0000   0.0189
 -10.500  -0.8172   0.03985   0.03518  -0.0558   1.0000   0.0194
 -10.250  -0.8104   0.03775   0.03289  -0.0549   1.0000   0.0199
 -10.000  -0.8036   0.03542   0.03030  -0.0537   1.0000   0.0205
  -9.750  -0.7960   0.03301   0.02758  -0.0523   1.0000   0.0213
  -9.500  -0.7868   0.03066   0.02483  -0.0506   1.0000   0.0223
  -9.250  -0.7748   0.02859   0.02231  -0.0490   1.0000   0.0236
  -9.000  -0.7593   0.02736   0.02100  -0.0477   1.0000   0.0246
  -8.750  -0.7415   0.02656   0.02014  -0.0465   1.0000   0.0256
  -8.500  -0.7242   0.02551   0.01893  -0.0452   1.0000   0.0268
  -8.250  -0.7066   0.02433   0.01752  -0.0438   1.0000   0.0284
  -8.000  -0.6879   0.02336   0.01625  -0.0424   1.0000   0.0300
  -7.750  -0.6700   0.02221   0.01502  -0.0411   1.0000   0.0315
  -7.500  -0.6505   0.02150   0.01426  -0.0400   1.0000   0.0330
  -7.250  -0.6305   0.02080   0.01345  -0.0388   1.0000   0.0348
  -7.000  -0.6100   0.02013   0.01261  -0.0376   1.0000   0.0369
  -6.750  -0.5893   0.01940   0.01173  -0.0365   1.0000   0.0384
  -6.500  -0.5691   0.01855   0.01085  -0.0354   1.0000   0.0403
  -6.250  -0.5356   0.01796   0.01020  -0.0370   0.9970   0.0430
  -6.000  -0.5013   0.01733   0.00946  -0.0386   0.9941   0.0454
  -5.750  -0.4679   0.01679   0.00879  -0.0399   0.9902   0.0476
  -5.500  -0.4340   0.01599   0.00799  -0.0416   0.9866   0.0506
  -5.250  -0.3996   0.01546   0.00742  -0.0432   0.9826   0.0533
  -5.000  -0.3656   0.01499   0.00688  -0.0446   0.9778   0.0567
  -4.750  -0.3294   0.01447   0.00633  -0.0465   0.9743   0.0611
  -4.500  -0.2974   0.01403   0.00588  -0.0475   0.9685   0.0664
  -4.250  -0.2624   0.01360   0.00544  -0.0491   0.9641   0.0741
  -4.000  -0.2284   0.01320   0.00505  -0.0505   0.9594   0.0865
  -3.750  -0.1972   0.01281   0.00474  -0.0513   0.9527   0.1052
  -3.500  -0.1626   0.01242   0.00445  -0.0528   0.9480   0.1312
  -3.250  -0.1336   0.01211   0.00422  -0.0531   0.9396   0.1579
  -3.000  -0.1004   0.01178   0.00399  -0.0542   0.9335   0.1883
  -2.750  -0.0716   0.01148   0.00381  -0.0545   0.9243   0.2218
  -2.500  -0.0397   0.01109   0.00362  -0.0553   0.9173   0.2760
  -2.250  -0.0124   0.01071   0.00348  -0.0553   0.9065   0.3364
  -2.000   0.0163   0.01036   0.00333  -0.0554   0.8966   0.3943
  -1.750   0.0450   0.00999   0.00319  -0.0555   0.8868   0.4613
  -1.500   0.0711   0.00964   0.00310  -0.0549   0.8745   0.5387
  -1.250   0.0969   0.00931   0.00304  -0.0542   0.8619   0.6195
  -1.000   0.1218   0.00900   0.00300  -0.0531   0.8488   0.7010
  -0.750   0.1461   0.00876   0.00299  -0.0516   0.8350   0.7792
  -0.500   0.1727   0.00863   0.00299  -0.0505   0.8206   0.8493
  -0.250   0.2058   0.00859   0.00296  -0.0509   0.8055   0.9051
   0.000   0.2434   0.00860   0.00291  -0.0525   0.7894   0.9449
   0.250   0.2822   0.00863   0.00285  -0.0545   0.7721   0.9724
   0.500   0.3224   0.00867   0.00279  -0.0570   0.7537   0.9917
   0.750   0.3566   0.00873   0.00274  -0.0583   0.7348   1.0000
   1.000   0.3814   0.00881   0.00272  -0.0575   0.7153   1.0000
   1.250   0.4062   0.00892   0.00272  -0.0568   0.6957   1.0000
   1.500   0.4310   0.00904   0.00274  -0.0560   0.6763   1.0000
   1.750   0.4558   0.00918   0.00277  -0.0553   0.6567   1.0000
   2.000   0.4806   0.00932   0.00284  -0.0546   0.6365   1.0000
   2.250   0.5054   0.00949   0.00291  -0.0539   0.6166   1.0000
   2.500   0.5303   0.00966   0.00299  -0.0532   0.5972   1.0000
   2.750   0.5553   0.00984   0.00311  -0.0525   0.5772   1.0000
   3.000   0.5802   0.01004   0.00323  -0.0519   0.5571   1.0000
   3.250   0.6050   0.01026   0.00336  -0.0512   0.5362   1.0000
   3.500   0.6295   0.01049   0.00352  -0.0505   0.5110   1.0000
   3.750   0.6540   0.01075   0.00368  -0.0497   0.4854   1.0000
   4.000   0.6782   0.01102   0.00386  -0.0490   0.4580   1.0000
   4.250   0.7021   0.01133   0.00406  -0.0482   0.4254   1.0000
   4.500   0.7251   0.01171   0.00427  -0.0474   0.3854   1.0000
   4.750   0.7479   0.01214   0.00452  -0.0465   0.3416   1.0000
   5.000   0.7706   0.01262   0.00483  -0.0457   0.2984   1.0000
   5.250   0.7926   0.01318   0.00519  -0.0448   0.2524   1.0000
   5.500   0.8143   0.01382   0.00560  -0.0440   0.2065   1.0000
   5.750   0.8362   0.01447   0.00606  -0.0431   0.1663   1.0000
   6.000   0.8578   0.01515   0.00659  -0.0423   0.1314   1.0000
   6.250   0.8794   0.01583   0.00713  -0.0415   0.1032   1.0000
   6.500   0.9013   0.01650   0.00771  -0.0406   0.0827   1.0000
   6.750   0.9230   0.01715   0.00832  -0.0397   0.0692   1.0000
   7.000   0.9448   0.01779   0.00897  -0.0388   0.0609   1.0000
   7.250   0.9659   0.01849   0.00966  -0.0379   0.0550   1.0000
   7.500   0.9873   0.01913   0.01037  -0.0369   0.0518   1.0000
   7.750   1.0083   0.01979   0.01110  -0.0359   0.0492   1.0000
   8.000   1.0284   0.02051   0.01189  -0.0348   0.0467   1.0000
   8.250   1.0463   0.02143   0.01283  -0.0335   0.0442   1.0000
   8.500   1.0656   0.02222   0.01370  -0.0323   0.0425   1.0000
   8.750   1.0847   0.02300   0.01459  -0.0311   0.0408   1.0000
   9.000   1.1033   0.02380   0.01547  -0.0299   0.0388   1.0000
   9.250   1.1209   0.02465   0.01638  -0.0286   0.0370   1.0000
   9.500   1.1356   0.02579   0.01756  -0.0270   0.0353   1.0000
   9.750   1.1511   0.02688   0.01875  -0.0255   0.0339   1.0000
  10.000   1.1677   0.02778   0.01980  -0.0241   0.0324   1.0000
  10.250   1.1824   0.02877   0.02091  -0.0225   0.0308   1.0000
  10.500   1.1950   0.02976   0.02198  -0.0207   0.0294   1.0000
  10.750   1.2059   0.03087   0.02314  -0.0188   0.0282   1.0000
  11.000   1.2144   0.03245   0.02479  -0.0168   0.0269   1.0000
  11.250   1.2256   0.03367   0.02622  -0.0150   0.0259   1.0000
  11.500   1.2352   0.03505   0.02779  -0.0133   0.0247   1.0000
  11.750   1.2434   0.03647   0.02935  -0.0117   0.0236   1.0000
  12.000   1.2506   0.03792   0.03091  -0.0102   0.0226   1.0000
  12.250   1.2563   0.03949   0.03256  -0.0088   0.0218   1.0000
  12.500   1.2595   0.04151   0.03465  -0.0076   0.0211   1.0000
  12.750   1.2623   0.04375   0.03712  -0.0064   0.0204   1.0000
  13.000   1.2634   0.04627   0.03988  -0.0054   0.0197   1.0000
  13.250   1.2627   0.04902   0.04288  -0.0047   0.0190   1.0000
  13.500   1.2608   0.05197   0.04603  -0.0045   0.0184   1.0000
  13.750   1.2581   0.05508   0.04933  -0.0046   0.0179   1.0000
  14.000   1.2547   0.05842   0.05282  -0.0051   0.0174   1.0000
  14.250   1.2507   0.06196   0.05650  -0.0061   0.0170   1.0000
  14.500   1.2456   0.06581   0.06048  -0.0073   0.0167   1.0000
  14.750   1.2394   0.06998   0.06477  -0.0089   0.0164   1.0000
  15.000   1.2306   0.07468   0.06959  -0.0109   0.0162   1.0000
  15.250   1.2190   0.08005   0.07508  -0.0132   0.0160   1.0000
  15.500   1.2022   0.08671   0.08198  -0.0165   0.0159   1.0000
  15.750   1.1831   0.09415   0.08964  -0.0204   0.0158   1.0000
  16.000   1.1624   0.10231   0.09801  -0.0249   0.0157   1.0000
  16.250   1.1396   0.11135   0.10725  -0.0301   0.0157   1.0000
  16.500   1.1143   0.12145   0.11752  -0.0361   0.0158   1.0000
  16.750   1.0860   0.13294   0.12918  -0.0430   0.0160   1.0000
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