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NACA M24 AIRFOIL (m24-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA M24 AIRFOIL (m24-il)
Reynolds number: 500,000
Max Cl/Cd: 104.16 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m24-il-500000.txt
Download as CSV file: xf-m24-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M24 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2239   0.08768   0.08449  -0.0106   0.6241   0.0249
  -8.000  -0.2197   0.08453   0.08131  -0.0114   0.6205   0.0251
  -7.750  -0.2163   0.08133   0.07808  -0.0124   0.6171   0.0255
  -7.500  -0.2140   0.07796   0.07473  -0.0138   0.6137   0.0258
  -7.250  -0.2132   0.07448   0.07127  -0.0157   0.6102   0.0262
  -7.000  -0.2139   0.07097   0.06773  -0.0176   0.6069   0.0266
  -6.750  -0.2145   0.06765   0.06438  -0.0186   0.6037   0.0271
  -6.500  -0.2098   0.06388   0.06056  -0.0206   0.6006   0.0279
  -6.250  -0.2026   0.05894   0.05549  -0.0264   0.5980   0.0288
  -6.000  -0.1906   0.05459   0.05104  -0.0285   0.5947   0.0289
  -5.750  -0.1850   0.04995   0.04639  -0.0280   0.5913   0.0292
  -5.500  -0.1726   0.04696   0.04334  -0.0278   0.5877   0.0295
  -5.250  -0.1585   0.04419   0.04051  -0.0279   0.5840   0.0298
  -5.000  -0.1429   0.04134   0.03762  -0.0282   0.5802   0.0302
  -4.750  -0.1261   0.03850   0.03472  -0.0286   0.5763   0.0309
  -4.500  -0.1081   0.03564   0.03175  -0.0291   0.5728   0.0317
  -4.250  -0.0880   0.03269   0.02863  -0.0296   0.5695   0.0333
  -4.000  -0.0635   0.02787   0.02349  -0.0302   0.5668   0.0347
  -3.750  -0.0474   0.02550   0.02111  -0.0299   0.5629   0.0352
  -3.500  -0.0280   0.02367   0.01923  -0.0296   0.5589   0.0356
  -3.250  -0.0074   0.02193   0.01738  -0.0294   0.5553   0.0363
  -3.000   0.0144   0.02017   0.01548  -0.0291   0.5518   0.0374
  -2.750   0.0464   0.01815   0.01307  -0.0283   0.5485   0.0411
  -2.500   0.0620   0.01515   0.00999  -0.0276   0.5450   0.0420
  -2.250   0.0842   0.01405   0.00882  -0.0274   0.5411   0.0426
  -2.000   0.1074   0.01306   0.00770  -0.0271   0.5376   0.0436
  -1.750   0.1321   0.01202   0.00656  -0.0268   0.5340   0.0456
  -1.500   0.1577   0.01024   0.00442  -0.0256   0.5307   0.0503
  -1.250   0.1822   0.00958   0.00372  -0.0255   0.5266   0.0514
  -1.000   0.2075   0.00897   0.00299  -0.0253   0.5230   0.0533
  -0.750   0.2342   0.00800   0.00164  -0.0244   0.5198   0.0600
  -0.500   0.2601   0.00747   0.00111  -0.0245   0.5160   0.0614
  -0.250   0.2966   0.01537   0.00779  -0.0224   0.5168   0.0418
   0.000   0.3256   0.01503   0.00737  -0.0225   0.5127   0.0412
   0.250   0.3546   0.01429   0.00651  -0.0226   0.5087   0.0413
   0.500   0.3833   0.01386   0.00595  -0.0227   0.5048   0.0411
   0.750   0.4122   0.01318   0.00526  -0.0229   0.5012   0.0409
   1.000   0.4405   0.01278   0.00484  -0.0229   0.4972   0.0411
   1.250   0.4675   0.01225   0.00427  -0.0227   0.4934   0.0418
   1.500   0.4941   0.01199   0.00397  -0.0225   0.4896   0.0428
   1.750   0.5214   0.01179   0.00381  -0.0224   0.4857   0.0441
   2.000   0.5488   0.01165   0.00369  -0.0224   0.4816   0.0456
   2.250   0.5763   0.01158   0.00361  -0.0223   0.4778   0.0481
   2.500   0.6032   0.01152   0.00351  -0.0222   0.4741   0.0512
   2.750   0.6308   0.01146   0.00349  -0.0223   0.4704   0.0573
   3.000   0.6576   0.01130   0.00353  -0.0221   0.4664   0.1117
   3.250   0.6842   0.01119   0.00360  -0.0221   0.4624   0.1943
   3.500   0.7083   0.00974   0.00397  -0.0213   0.4587   0.9532
   3.750   0.7840   0.01035   0.00456  -0.0315   0.4535   0.9786
   4.000   0.8898   0.01078   0.00491  -0.0484   0.4473   0.9959
   4.250   0.9405   0.01089   0.00493  -0.0537   0.4428   1.0000
   4.500   0.9670   0.01096   0.00501  -0.0537   0.4391   1.0000
   4.750   0.9935   0.01102   0.00509  -0.0537   0.4350   1.0000
   5.000   1.0197   0.01111   0.00515  -0.0537   0.4311   1.0000
   5.250   1.0459   0.01127   0.00526  -0.0537   0.4273   1.0000
   5.500   1.0721   0.01137   0.00539  -0.0537   0.4239   1.0000
   5.750   1.0981   0.01147   0.00551  -0.0536   0.4201   1.0000
   6.000   1.1240   0.01158   0.00563  -0.0536   0.4165   1.0000
   6.250   1.1496   0.01176   0.00577  -0.0535   0.4129   1.0000
   6.500   1.1752   0.01191   0.00595  -0.0534   0.4092   1.0000
   6.750   1.2006   0.01201   0.00610  -0.0533   0.4048   1.0000
   7.000   1.2256   0.01214   0.00623  -0.0532   0.3995   1.0000
   7.250   1.2503   0.01232   0.00641  -0.0530   0.3941   1.0000
   7.500   1.2751   0.01244   0.00659  -0.0528   0.3893   1.0000
   7.750   1.2993   0.01261   0.00677  -0.0525   0.3843   1.0000
   8.000   1.3229   0.01279   0.00697  -0.0522   0.3776   1.0000
   8.250   1.3466   0.01295   0.00716  -0.0519   0.3703   1.0000
   8.500   1.3694   0.01320   0.00740  -0.0514   0.3641   1.0000
   8.750   1.3926   0.01337   0.00765  -0.0511   0.3575   1.0000
   9.000   1.4142   0.01366   0.00793  -0.0505   0.3487   1.0000
   9.250   1.4357   0.01393   0.00822  -0.0499   0.3386   1.0000
   9.500   1.4562   0.01424   0.00856  -0.0491   0.3276   1.0000
   9.750   1.4746   0.01469   0.00899  -0.0481   0.3128   1.0000
  10.000   1.4889   0.01536   0.00958  -0.0466   0.2921   1.0000
  10.250   1.4937   0.01651   0.01054  -0.0439   0.2551   1.0000
  10.500   1.4757   0.01855   0.01228  -0.0381   0.2063   1.0000
  10.750   1.4477   0.02023   0.01391  -0.0306   0.1892   1.0000
  11.000   1.4207   0.02282   0.01639  -0.0250   0.1661   1.0000
  11.250   1.3954   0.02618   0.01962  -0.0211   0.1391   1.0000
  11.500   1.3675   0.03038   0.02368  -0.0182   0.1050   1.0000
  11.750   1.3425   0.03478   0.02796  -0.0162   0.0801   1.0000
  12.000   1.3213   0.03910   0.03222  -0.0147   0.0571   1.0000
  12.250   1.2984   0.04377   0.03680  -0.0135   0.0360   1.0000
  12.500   1.2875   0.04744   0.04048  -0.0128   0.0293   1.0000
  12.750   1.2812   0.05082   0.04391  -0.0124   0.0262   1.0000
  13.000   1.2794   0.05378   0.04695  -0.0122   0.0248   1.0000
  13.250   1.2765   0.05694   0.05019  -0.0120   0.0238   1.0000
  13.500   1.2724   0.06031   0.05363  -0.0119   0.0228   1.0000
  13.750   1.2664   0.06394   0.05735  -0.0119   0.0219   1.0000
  14.000   1.2608   0.06762   0.06112  -0.0120   0.0213   1.0000
  14.250   1.2587   0.07094   0.06452  -0.0121   0.0209   1.0000
  14.500   1.2556   0.07439   0.06806  -0.0123   0.0205   1.0000
  14.750   1.2521   0.07794   0.07169  -0.0126   0.0200   1.0000
  15.000   1.2480   0.08163   0.07545  -0.0130   0.0195   1.0000
  15.250   1.2438   0.08536   0.07925  -0.0134   0.0191   1.0000
  15.500   1.2389   0.08921   0.08318  -0.0138   0.0186   1.0000
  15.750   1.2328   0.09327   0.08731  -0.0144   0.0182   1.0000
  16.000   1.2254   0.09753   0.09163  -0.0150   0.0178   1.0000
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