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NACA M22 AIRFOIL (m22-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA M22 AIRFOIL (m22-il)
Reynolds number: 200,000
Max Cl/Cd: 73.91 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m22-il-200000-n5.txt
Download as CSV file: xf-m22-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4274   0.11838   0.11470   0.0274   0.6962   0.0151
  -8.000  -0.4221   0.11582   0.11214   0.0245   0.6909   0.0152
  -7.750  -0.4167   0.11331   0.10961   0.0213   0.6853   0.0152
  -7.500  -0.4064   0.11030   0.10656   0.0176   0.6804   0.0153
  -7.250  -0.3942   0.10683   0.10307   0.0144   0.6751   0.0153
  -7.000  -0.3878   0.10042   0.09667   0.0156   0.6702   0.0155
  -6.750  -0.3796   0.09584   0.09204   0.0157   0.6656   0.0158
  -6.500  -0.3685   0.09210   0.08828   0.0141   0.6602   0.0161
  -6.250  -0.3555   0.08862   0.08476   0.0119   0.6549   0.0165
  -5.750  -0.3238   0.08185   0.07789   0.0067   0.6449   0.0175
  -5.500  -0.3054   0.07849   0.07445   0.0038   0.6399   0.0182
  -5.250  -0.2851   0.07519   0.07105   0.0009   0.6356   0.0195
  -5.000  -0.2571   0.07234   0.06811  -0.0032   0.6299   0.0217
  -4.750  -0.2254   0.06969   0.06531  -0.0077   0.6250   0.0223
  -4.500  -0.1988   0.06635   0.06183  -0.0107   0.6207   0.0224
  -4.250  -0.1740   0.06267   0.05805  -0.0130   0.6155   0.0224
  -4.000  -0.1508   0.05883   0.05409  -0.0147   0.6108   0.0223
  -3.750  -0.1330   0.05464   0.04981  -0.0156   0.6067   0.0215
  -3.500  -0.0867   0.05295   0.04782  -0.0194   0.6014   0.0228
  -3.250  -0.0696   0.04802   0.04279  -0.0202   0.5970   0.0237
  -3.000  -0.0506   0.04552   0.04019  -0.0205   0.5928   0.0253
  -2.750  -0.0125   0.04460   0.03905  -0.0223   0.5872   0.0321
  -2.500   0.0219   0.04254   0.03671  -0.0233   0.5826   0.0326
  -2.250   0.0506   0.03990   0.03381  -0.0238   0.5787   0.0327
  -2.000   0.0736   0.03566   0.02943  -0.0246   0.5741   0.0338
  -1.750   0.0944   0.03392   0.02765  -0.0250   0.5690   0.0373
  -1.500   0.1334   0.03372   0.02702  -0.0251   0.5649   0.0443
  -1.250   0.1605   0.03056   0.02363  -0.0255   0.5604   0.0453
  -1.000   0.1840   0.02849   0.02151  -0.0260   0.5556   0.0471
  -0.750   0.2177   0.02910   0.02174  -0.0258   0.5512   0.0575
  -0.500   0.2430   0.02613   0.01864  -0.0263   0.5470   0.0590
   0.000   0.3015   0.02234   0.01436  -0.0260   0.5381   0.0423
   0.250   0.3302   0.02094   0.01269  -0.0260   0.5343   0.0411
   0.500   0.3595   0.01970   0.01123  -0.0260   0.5295   0.0409
   0.750   0.3885   0.01872   0.01003  -0.0259   0.5251   0.0417
   1.000   0.4174   0.01842   0.00946  -0.0258   0.5212   0.0444
   1.250   0.4459   0.01733   0.00825  -0.0260   0.5166   0.0432
   1.500   0.4744   0.01659   0.00738  -0.0261   0.5120   0.0422
   1.750   0.5027   0.01601   0.00666  -0.0261   0.5081   0.0414
   2.000   0.5308   0.01552   0.00608  -0.0261   0.5040   0.0406
   2.250   0.5588   0.01511   0.00563  -0.0262   0.4992   0.0400
   2.500   0.5862   0.01477   0.00524  -0.0261   0.4949   0.0395
   2.750   0.6134   0.01452   0.00494  -0.0261   0.4913   0.0392
   3.000   0.6408   0.01431   0.00478  -0.0261   0.4866   0.0391
   3.250   0.6680   0.01416   0.00465  -0.0261   0.4821   0.0392
   3.500   0.6952   0.01407   0.00453  -0.0261   0.4782   0.0395
   3.750   0.7223   0.01402   0.00450  -0.0261   0.4737   0.0402
   4.000   0.7497   0.01402   0.00452  -0.0262   0.4692   0.0414
   4.250   0.7772   0.01406   0.00453  -0.0263   0.4653   0.0436
   4.500   0.8047   0.01411   0.00463  -0.0264   0.4613   0.0532
   5.000   0.8964   0.01302   0.00527  -0.0349   0.4496   1.0000
   5.250   0.9224   0.01306   0.00528  -0.0347   0.4340   1.0000
   5.500   0.9484   0.01317   0.00545  -0.0346   0.4216   1.0000
   5.750   0.9744   0.01330   0.00559  -0.0345   0.4034   1.0000
   6.000   1.0000   0.01353   0.00576  -0.0345   0.3769   1.0000
   6.250   1.0239   0.01432   0.00616  -0.0348   0.2987   1.0000
   6.500   1.0334   0.01888   0.00919  -0.0364   0.0259   1.0000
   6.750   1.0555   0.01964   0.01006  -0.0361   0.0204   1.0000
   7.000   1.0767   0.02045   0.01104  -0.0357   0.0174   1.0000
   7.250   1.0963   0.02143   0.01221  -0.0352   0.0158   1.0000
   7.500   1.1131   0.02270   0.01368  -0.0346   0.0146   1.0000
   7.750   1.1224   0.02469   0.01591  -0.0338   0.0131   1.0000
   8.000   1.1297   0.02661   0.01801  -0.0330   0.0121   1.0000
   8.250   1.1349   0.02869   0.02022  -0.0326   0.0117   1.0000
   8.500   1.1327   0.03102   0.02266  -0.0313   0.0115   1.0000
   8.750   1.1318   0.03347   0.02519  -0.0303   0.0112   1.0000
   9.000   1.1322   0.03592   0.02772  -0.0294   0.0109   1.0000
   9.250   1.1335   0.03828   0.03014  -0.0284   0.0107   1.0000
   9.500   1.1364   0.04046   0.03238  -0.0272   0.0105   1.0000
   9.750   1.1415   0.04238   0.03435  -0.0257   0.0103   1.0000
  10.000   1.1491   0.04408   0.03610  -0.0243   0.0098   1.0000
  10.250   1.1575   0.04574   0.03780  -0.0231   0.0090   1.0000
  10.500   1.1660   0.04740   0.03952  -0.0219   0.0084   1.0000
  10.750   1.1782   0.04878   0.04089  -0.0198   0.0079   1.0000
  11.000   1.2031   0.04976   0.04187  -0.0162   0.0077   1.0000
  11.250   1.2283   0.05165   0.04388  -0.0137   0.0075   1.0000
  11.500   1.2407   0.05398   0.04641  -0.0124   0.0075   1.0000
  11.750   1.2511   0.05666   0.04930  -0.0112   0.0074   1.0000
  12.000   1.2595   0.05974   0.05260  -0.0101   0.0074   1.0000
  12.500   1.2704   0.06659   0.05987  -0.0084   0.0076   1.0000
  12.750   1.2662   0.06974   0.06322  -0.0081   0.0076   1.0000
  13.000   1.2602   0.07301   0.06670  -0.0081   0.0077   1.0000
  13.250   1.2528   0.07649   0.07040  -0.0083   0.0078   1.0000
  13.500   1.2436   0.08046   0.07458  -0.0087   0.0079   1.0000
  13.750   1.2330   0.08482   0.07914  -0.0095   0.0079   1.0000
  14.000   1.2210   0.08949   0.08401  -0.0105   0.0079   1.0000
  14.250   1.2081   0.09440   0.08916  -0.0118   0.0078   1.0000
  14.500   1.1944   0.09949   0.09442  -0.0135   0.0078   1.0000
  14.750   1.1799   0.10495   0.10005  -0.0155   0.0078   1.0000
  15.000   1.1658   0.11061   0.10588  -0.0180   0.0078   1.0000
  15.250   1.1518   0.11662   0.11206  -0.0209   0.0078   1.0000
  15.500   1.1382   0.12282   0.11844  -0.0243   0.0079   1.0000
  15.750   1.1245   0.12950   0.12528  -0.0281   0.0079   1.0000
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