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NACA M22 AIRFOIL (m22-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA M22 AIRFOIL (m22-il)
Reynolds number: 1,000,000
Max Cl/Cd: 91.02 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m22-il-1000000-n5.txt
Download as CSV file: xf-m22-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4473   0.10991   0.10729   0.0350   0.5882   0.0039
  -7.750  -0.4472   0.10439   0.10179   0.0325   0.5849   0.0029
  -7.500  -0.4430   0.10106   0.09845   0.0303   0.5806   0.0029
  -7.250  -0.4353   0.09740   0.09477   0.0274   0.5768   0.0029
  -7.000  -0.4244   0.09335   0.09071   0.0240   0.5727   0.0029
  -6.750  -0.4120   0.08913   0.08647   0.0204   0.5683   0.0030
  -6.500  -0.3967   0.08581   0.08311   0.0172   0.5639   0.0031
  -6.250  -0.3800   0.08254   0.07981   0.0142   0.5598   0.0032
  -6.000  -0.3619   0.07923   0.07646   0.0112   0.5554   0.0034
  -5.750  -0.3424   0.07554   0.07272   0.0079   0.5511   0.0036
  -5.500  -0.3214   0.07160   0.06872   0.0045   0.5473   0.0038
  -5.250  -0.2987   0.06733   0.06439   0.0010   0.5433   0.0042
  -5.000  -0.2737   0.06217   0.05914  -0.0028   0.5395   0.0045
  -4.750  -0.2470   0.05700   0.05387  -0.0065   0.5360   0.0049
  -4.500  -0.2217   0.05435   0.05113  -0.0085   0.5322   0.0051
  -4.250  -0.1954   0.05143   0.04813  -0.0105   0.5278   0.0055
  -4.000  -0.1669   0.04734   0.04390  -0.0129   0.5239   0.0063
  -3.750  -0.1374   0.04289   0.03930  -0.0150   0.5204   0.0074
  -3.500  -0.1107   0.04117   0.03750  -0.0160   0.5166   0.0079
  -3.250  -0.0825   0.03854   0.03475  -0.0171   0.5125   0.0088
  -3.000  -0.0513   0.03373   0.02970  -0.0183   0.5090   0.0107
  -2.750  -0.0245   0.03292   0.02881  -0.0189   0.5050   0.0112
  -2.500   0.0031   0.03148   0.02728  -0.0194   0.5011   0.0121
  -2.250   0.0367   0.02550   0.02091  -0.0196   0.4980   0.0157
  -2.000   0.0637   0.02513   0.02047  -0.0199   0.4936   0.0161
  -1.750   0.0910   0.02444   0.01971  -0.0203   0.4901   0.0165
  -1.500   0.1187   0.02351   0.01869  -0.0206   0.4862   0.0172
  -1.250   0.1469   0.02243   0.01749  -0.0208   0.4820   0.0184
  -1.000   0.1759   0.02077   0.01565  -0.0208   0.4781   0.0195
  -0.750   0.2052   0.01886   0.01354  -0.0207   0.4751   0.0201
  -0.500   0.2344   0.01678   0.01122  -0.0204   0.4717   0.0209
  -0.250   0.2635   0.01453   0.00867  -0.0200   0.4679   0.0219
   0.000   0.2918   0.01325   0.00712  -0.0200   0.4639   0.0237
   0.250   0.3198   0.01266   0.00646  -0.0202   0.4604   0.0247
   0.500   0.3480   0.01242   0.00617  -0.0205   0.4567   0.0257
   0.750   0.3763   0.01208   0.00577  -0.0207   0.4526   0.0266
   1.000   0.4047   0.01170   0.00530  -0.0209   0.4485   0.0276
   1.250   0.4331   0.01123   0.00475  -0.0210   0.4448   0.0281
   1.500   0.4615   0.01077   0.00420  -0.0211   0.4409   0.0281
   1.750   0.4898   0.01046   0.00383  -0.0213   0.4370   0.0285
   2.000   0.5181   0.01017   0.00349  -0.0215   0.4334   0.0289
   2.250   0.5462   0.00982   0.00310  -0.0216   0.4296   0.0283
   2.500   0.5741   0.00952   0.00277  -0.0217   0.4252   0.0277
   2.750   0.6020   0.00931   0.00251  -0.0218   0.4209   0.0271
   3.000   0.6299   0.00912   0.00231  -0.0219   0.4175   0.0266
   3.250   0.6579   0.00898   0.00217  -0.0220   0.4137   0.0262
   3.500   0.6859   0.00890   0.00207  -0.0222   0.4095   0.0259
   3.750   0.7141   0.00887   0.00203  -0.0225   0.4053   0.0256
   4.000   0.7423   0.00885   0.00201  -0.0227   0.3962   0.0254
   4.250   0.7704   0.00891   0.00202  -0.0230   0.3829   0.0254
   4.500   0.7987   0.00896   0.00206  -0.0234   0.3745   0.0254
   4.750   0.8268   0.00913   0.00215  -0.0238   0.3531   0.0256
   5.000   0.8547   0.00939   0.00229  -0.0242   0.3255   0.0264
   5.250   0.8822   0.00998   0.00261  -0.0249   0.2710   0.0295
   5.500   0.9053   0.01286   0.00436  -0.0268   0.0212   0.0331
   5.750   0.9325   0.01308   0.00466  -0.0271   0.0148   0.0786
   6.000   0.9587   0.01299   0.00510  -0.0274   0.0120   0.4432
   6.250   0.9808   0.01205   0.00543  -0.0265   0.0107   0.9861
   6.500   1.0476   0.01278   0.00623  -0.0361   0.0075   1.0000
   6.750   1.0720   0.01311   0.00657  -0.0359   0.0069   1.0000
   7.000   1.0962   0.01349   0.00699  -0.0357   0.0061   1.0000
   7.250   1.1202   0.01391   0.00742  -0.0355   0.0055   1.0000
   7.500   1.1431   0.01455   0.00813  -0.0353   0.0048   1.0000
   7.750   1.1662   0.01505   0.00868  -0.0351   0.0045   1.0000
   8.000   1.1889   0.01558   0.00924  -0.0348   0.0040   1.0000
   8.250   1.2107   0.01622   0.00995  -0.0345   0.0037   1.0000
   8.500   1.2319   0.01687   0.01065  -0.0341   0.0035   1.0000
   8.750   1.2523   0.01757   0.01139  -0.0337   0.0033   1.0000
   9.000   1.2702   0.01853   0.01244  -0.0332   0.0030   1.0000
   9.250   1.2828   0.02001   0.01403  -0.0324   0.0028   1.0000
   9.500   1.2967   0.02119   0.01532  -0.0317   0.0028   1.0000
   9.750   1.3064   0.02292   0.01716  -0.0315   0.0027   1.0000
  10.000   1.3070   0.02520   0.01956  -0.0310   0.0026   1.0000
  10.250   1.3076   0.02770   0.02216  -0.0305   0.0025   1.0000
  10.500   1.3080   0.03033   0.02490  -0.0301   0.0024   1.0000
  10.750   1.3094   0.03284   0.02749  -0.0297   0.0023   1.0000
  11.000   1.3113   0.03527   0.03002  -0.0292   0.0022   1.0000
  11.250   1.3149   0.03754   0.03236  -0.0287   0.0021   1.0000
  11.500   1.3177   0.03984   0.03474  -0.0282   0.0020   1.0000
  11.750   1.3238   0.04189   0.03685  -0.0280   0.0020   1.0000
  12.000   1.3277   0.04412   0.03917  -0.0277   0.0019   1.0000
  12.250   1.3306   0.04644   0.04157  -0.0272   0.0018   1.0000
  12.500   1.3327   0.04883   0.04404  -0.0267   0.0018   1.0000
  12.750   1.3352   0.05120   0.04649  -0.0263   0.0018   1.0000
  13.000   1.3369   0.05366   0.04904  -0.0258   0.0017   1.0000
  13.250   1.3377   0.05622   0.05170  -0.0252   0.0017   1.0000
  13.500   1.3371   0.05894   0.05455  -0.0243   0.0016   1.0000
  13.750   1.3315   0.06201   0.05783  -0.0217   0.0016   1.0000
  14.000   1.3314   0.06487   0.06087  -0.0202   0.0015   1.0000
  14.250   1.3249   0.06907   0.06537  -0.0165   0.0014   1.0000
  14.500   1.3098   0.07511   0.07171  -0.0149   0.0013   1.0000
  14.750   1.2914   0.08146   0.07829  -0.0155   0.0013   1.0000
  15.000   1.2737   0.08770   0.08472  -0.0169   0.0012   1.0000
  15.250   1.2559   0.09423   0.09143  -0.0188   0.0012   1.0000
  15.500   1.2383   0.10094   0.09830  -0.0213   0.0012   1.0000
  15.750   1.2199   0.10807   0.10558  -0.0242   0.0012   1.0000
  16.000   1.2023   0.11540   0.11306  -0.0276   0.0012   1.0000
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