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NACA M22 AIRFOIL (m22-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA M22 AIRFOIL (m22-il)
Reynolds number: 500,000
Max Cl/Cd: 81.88 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m22-il-500000-n5.txt
Download as CSV file: xf-m22-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M22 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4380   0.11050   0.10749   0.0321   0.6297   0.0071
  -7.750  -0.4321   0.10710   0.10408   0.0303   0.6251   0.0071
  -7.250  -0.4214   0.10033   0.09730   0.0268   0.6161   0.0070
  -7.000  -0.4126   0.09716   0.09410   0.0248   0.6111   0.0064
  -6.750  -0.4012   0.09351   0.09041   0.0217   0.6067   0.0061
  -6.500  -0.3879   0.08971   0.08660   0.0185   0.6021   0.0060
  -6.250  -0.3729   0.08589   0.08274   0.0152   0.5975   0.0060
  -5.750  -0.3361   0.07751   0.07426   0.0077   0.5891   0.0069
  -5.500  -0.3145   0.07330   0.06999   0.0039   0.5845   0.0071
  -5.250  -0.2939   0.06948   0.06609   0.0009   0.5800   0.0070
  -5.000  -0.2708   0.06546   0.06200  -0.0022   0.5758   0.0070
  -4.750  -0.2454   0.06108   0.05750  -0.0055   0.5715   0.0071
  -4.500  -0.2211   0.05793   0.05426  -0.0079   0.5668   0.0074
  -4.250  -0.1960   0.05539   0.05163  -0.0099   0.5624   0.0078
  -4.000  -0.1695   0.05250   0.04865  -0.0119   0.5577   0.0085
  -3.750  -0.1396   0.04838   0.04437  -0.0144   0.5536   0.0099
  -3.250  -0.0826   0.04209   0.03780  -0.0175   0.5453   0.0111
  -3.000  -0.0554   0.04027   0.03586  -0.0185   0.5406   0.0121
  -2.750  -0.0238   0.03681   0.03218  -0.0197   0.5367   0.0143
  -2.500   0.0084   0.03298   0.02809  -0.0206   0.5333   0.0158
  -2.250   0.0333   0.03250   0.02758  -0.0210   0.5284   0.0167
  -2.000   0.0609   0.03121   0.02617  -0.0216   0.5239   0.0183
  -1.750   0.0906   0.02907   0.02381  -0.0219   0.5201   0.0195
  -1.500   0.1227   0.02672   0.02123  -0.0220   0.5163   0.0217
  -1.250   0.1516   0.02475   0.01906  -0.0222   0.5120   0.0242
  -1.000   0.1781   0.02391   0.01812  -0.0226   0.5078   0.0254
  -0.750   0.2064   0.02268   0.01675  -0.0228   0.5041   0.0266
  -0.500   0.2354   0.02124   0.01514  -0.0228   0.5001   0.0274
  -0.250   0.2645   0.02000   0.01371  -0.0229   0.4958   0.0289
   0.000   0.2939   0.01819   0.01163  -0.0227   0.4922   0.0276
   0.250   0.3233   0.01654   0.00975  -0.0225   0.4887   0.0276
   0.500   0.3522   0.01531   0.00829  -0.0224   0.4848   0.0289
   0.750   0.3809   0.01443   0.00722  -0.0224   0.4807   0.0300
   1.000   0.4095   0.01379   0.00642  -0.0225   0.4768   0.0306
   1.250   0.4379   0.01326   0.00579  -0.0226   0.4728   0.0310
   1.500   0.4664   0.01301   0.00546  -0.0228   0.4688   0.0319
   1.750   0.4947   0.01253   0.00489  -0.0229   0.4648   0.0319
   2.000   0.5228   0.01200   0.00428  -0.0230   0.4610   0.0313
   2.250   0.5509   0.01160   0.00384  -0.0231   0.4567   0.0309
   2.500   0.5787   0.01129   0.00349  -0.0231   0.4526   0.0306
   2.750   0.6064   0.01106   0.00322  -0.0232   0.4490   0.0302
   3.000   0.6341   0.01085   0.00302  -0.0233   0.4452   0.0300
   3.250   0.6618   0.01069   0.00287  -0.0234   0.4409   0.0298
   3.500   0.6895   0.01060   0.00276  -0.0235   0.4365   0.0296
   3.750   0.7174   0.01053   0.00271  -0.0237   0.4326   0.0296
   4.000   0.7453   0.01048   0.00270  -0.0239   0.4286   0.0296
   4.250   0.7733   0.01047   0.00271  -0.0241   0.4245   0.0299
   4.500   0.8013   0.01051   0.00273  -0.0244   0.4158   0.0303
   4.750   0.8293   0.01058   0.00277  -0.0247   0.4012   0.0312
   5.000   0.8573   0.01069   0.00285  -0.0250   0.3911   0.0328
   5.250   0.8851   0.01081   0.00298  -0.0253   0.3724   0.0479
   5.750   0.9678   0.01370   0.00593  -0.0365   0.0252   1.0000
   6.250   1.0171   0.01461   0.00692  -0.0362   0.0125   1.0000
   6.500   1.0414   0.01503   0.00743  -0.0360   0.0115   1.0000
   6.750   1.0652   0.01554   0.00803  -0.0358   0.0102   1.0000
   7.000   1.0884   0.01613   0.00866  -0.0356   0.0087   1.0000
   7.250   1.1088   0.01728   0.00995  -0.0354   0.0075   1.0000
   7.500   1.1301   0.01804   0.01078  -0.0350   0.0072   1.0000
   7.750   1.1495   0.01902   0.01188  -0.0346   0.0067   1.0000
   8.000   1.1667   0.02015   0.01311  -0.0340   0.0063   1.0000
   8.250   1.1834   0.02116   0.01419  -0.0334   0.0057   1.0000
   8.500   1.1997   0.02212   0.01519  -0.0328   0.0052   1.0000
   8.750   1.2085   0.02382   0.01697  -0.0321   0.0049   1.0000
   9.000   1.2065   0.02648   0.01974  -0.0316   0.0047   1.0000
   9.250   1.2081   0.02862   0.02198  -0.0307   0.0046   1.0000
   9.500   1.2105   0.03091   0.02437  -0.0300   0.0045   1.0000
   9.750   1.2122   0.03329   0.02687  -0.0292   0.0043   1.0000
  10.000   1.2141   0.03562   0.02929  -0.0283   0.0042   1.0000
  10.250   1.2169   0.03781   0.03156  -0.0271   0.0040   1.0000
  10.500   1.2211   0.03980   0.03363  -0.0256   0.0039   1.0000
  10.750   1.2275   0.04156   0.03546  -0.0238   0.0038   1.0000
  11.000   1.2363   0.04312   0.03711  -0.0217   0.0037   1.0000
  11.250   1.2477   0.04461   0.03868  -0.0195   0.0036   1.0000
  11.500   1.2587   0.04628   0.04047  -0.0178   0.0035   1.0000
  11.750   1.2658   0.04823   0.04250  -0.0172   0.0033   1.0000
  12.000   1.2714   0.05034   0.04471  -0.0169   0.0032   1.0000
  12.250   1.2749   0.05266   0.04712  -0.0168   0.0031   1.0000
  12.500   1.2771   0.05521   0.04978  -0.0164   0.0030   1.0000
  12.750   1.2801   0.05815   0.05293  -0.0150   0.0028   1.0000
  13.000   1.2826   0.06134   0.05638  -0.0138   0.0027   1.0000
  13.250   1.2811   0.06503   0.06030  -0.0129   0.0027   1.0000
  13.500   1.2768   0.06916   0.06465  -0.0124   0.0026   1.0000
  13.750   1.2685   0.07361   0.06930  -0.0125   0.0026   1.0000
  14.000   1.2576   0.07842   0.07431  -0.0131   0.0025   1.0000
  14.250   1.2450   0.08348   0.07956  -0.0140   0.0025   1.0000
  14.500   1.2315   0.08890   0.08516  -0.0155   0.0025   1.0000
  14.750   1.2172   0.09472   0.09116  -0.0173   0.0025   1.0000
  15.000   1.2026   0.10079   0.09740  -0.0196   0.0025   1.0000
  15.250   1.1875   0.10724   0.10400  -0.0223   0.0025   1.0000
  15.500   1.1724   0.11398   0.11089  -0.0254   0.0025   1.0000
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