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NACA M18 AIRFOIL (m18-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA M18 AIRFOIL (m18-il)
Reynolds number: 500,000
Max Cl/Cd: 100.71 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m18-il-500000-n5.txt
Download as CSV file: xf-m18-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M18 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4463   0.08469   0.08168  -0.0183   0.7374   0.0213
  -8.500  -0.4530   0.07939   0.07635  -0.0233   0.7276   0.0214
  -8.000  -0.4615   0.06905   0.06585  -0.0300   0.7097   0.0219
  -7.500  -0.5320   0.03197   0.02730  -0.0354   0.7038   0.0241
  -7.250  -0.5159   0.02958   0.02464  -0.0344   0.6953   0.0243
  -7.000  -0.4985   0.02734   0.02209  -0.0334   0.6869   0.0245
  -6.750  -0.4791   0.02544   0.01990  -0.0325   0.6790   0.0248
  -6.500  -0.4581   0.02382   0.01800  -0.0316   0.6711   0.0250
  -6.250  -0.4358   0.02239   0.01631  -0.0309   0.6642   0.0252
  -6.000  -0.4125   0.02114   0.01483  -0.0303   0.6574   0.0254
  -5.750  -0.3883   0.02004   0.01350  -0.0298   0.6513   0.0257
  -5.500  -0.3633   0.01905   0.01231  -0.0294   0.6449   0.0259
  -5.250  -0.3379   0.01815   0.01121  -0.0290   0.6386   0.0262
  -5.000  -0.3117   0.01742   0.01032  -0.0287   0.6327   0.0266
  -4.750  -0.2851   0.01677   0.00953  -0.0284   0.6269   0.0270
  -4.500  -0.2584   0.01614   0.00874  -0.0282   0.6215   0.0273
  -4.250  -0.2314   0.01552   0.00799  -0.0280   0.6166   0.0276
  -4.000  -0.2041   0.01498   0.00735  -0.0279   0.6111   0.0279
  -3.750  -0.1768   0.01453   0.00678  -0.0277   0.6054   0.0281
  -3.500  -0.1493   0.01411   0.00628  -0.0276   0.6001   0.0283
  -3.250  -0.1217   0.01373   0.00583  -0.0275   0.5942   0.0285
  -3.000  -0.0942   0.01341   0.00543  -0.0274   0.5888   0.0287
  -2.750  -0.0674   0.01285   0.00483  -0.0272   0.5839   0.0292
  -2.500  -0.0402   0.01246   0.00442  -0.0270   0.5783   0.0296
  -2.250  -0.0130   0.01217   0.00409  -0.0269   0.5727   0.0300
  -2.000   0.0145   0.01192   0.00383  -0.0268   0.5672   0.0305
  -1.750   0.0420   0.01170   0.00359  -0.0267   0.5607   0.0311
  -1.500   0.0695   0.01153   0.00338  -0.0266   0.5545   0.0318
  -1.250   0.0972   0.01135   0.00319  -0.0265   0.5479   0.0326
  -1.000   0.1248   0.01119   0.00300  -0.0265   0.5414   0.0333
  -0.750   0.1525   0.01105   0.00283  -0.0264   0.5353   0.0339
  -0.500   0.1802   0.01093   0.00268  -0.0264   0.5283   0.0345
  -0.250   0.2077   0.01080   0.00252  -0.0263   0.5219   0.0357
   0.000   0.2355   0.01068   0.00241  -0.0262   0.5148   0.0372
   0.500   0.2910   0.01056   0.00224  -0.0262   0.5003   0.0417
   0.750   0.3184   0.01048   0.00219  -0.0262   0.4931   0.0518
   1.000   0.3458   0.01036   0.00217  -0.0261   0.4870   0.0829
   1.250   0.3730   0.01026   0.00217  -0.0261   0.4807   0.1169
   1.500   0.4001   0.01018   0.00219  -0.0260   0.4751   0.1603
   1.750   0.4268   0.01001   0.00222  -0.0259   0.4693   0.2318
   2.000   0.4364   0.00839   0.00214  -0.0227   0.4643   0.7605
   2.250   0.4735   0.00828   0.00252  -0.0240   0.4588   0.9413
   2.500   0.5088   0.00848   0.00270  -0.0254   0.4538   0.9612
   2.750   0.5557   0.00878   0.00294  -0.0295   0.4472   0.9747
   3.000   0.6002   0.00902   0.00312  -0.0331   0.4405   0.9824
   3.250   0.6476   0.00921   0.00325  -0.0374   0.4330   0.9868
   3.500   0.6847   0.00934   0.00334  -0.0396   0.4273   0.9895
   3.750   0.7155   0.00942   0.00341  -0.0404   0.4227   0.9909
   4.000   0.7453   0.00951   0.00348  -0.0410   0.4182   0.9923
   4.250   0.7745   0.00964   0.00358  -0.0415   0.4142   0.9935
   4.500   0.8050   0.00972   0.00366  -0.0422   0.4108   0.9943
   4.750   0.8358   0.00980   0.00375  -0.0431   0.4062   0.9950
   5.000   0.8662   0.00991   0.00385  -0.0438   0.4010   0.9958
   5.250   0.8963   0.01004   0.00396  -0.0446   0.3963   0.9967
   5.500   0.9270   0.01012   0.00408  -0.0454   0.3916   0.9977
   5.750   0.9574   0.01024   0.00421  -0.0462   0.3863   0.9987
   6.000   0.9873   0.01040   0.00436  -0.0470   0.3816   0.9995
   6.250   1.0155   0.01050   0.00451  -0.0473   0.3775   1.0000
   6.500   1.0400   0.01062   0.00466  -0.0468   0.3725   1.0000
   6.750   1.0640   0.01078   0.00482  -0.0463   0.3670   1.0000
   7.000   1.0882   0.01091   0.00500  -0.0458   0.3611   1.0000
   7.250   1.1117   0.01109   0.00518  -0.0451   0.3522   1.0000
   7.500   1.1350   0.01127   0.00536  -0.0445   0.3405   1.0000
   7.750   1.1565   0.01158   0.00560  -0.0436   0.3197   1.0000
   8.000   1.1753   0.01211   0.00595  -0.0424   0.2830   1.0000
   8.250   1.1928   0.01272   0.00640  -0.0410   0.2531   1.0000
   8.500   1.2095   0.01334   0.00690  -0.0395   0.2289   1.0000
   8.750   1.2253   0.01398   0.00743  -0.0377   0.2048   1.0000
   9.000   1.2386   0.01474   0.00805  -0.0357   0.1748   1.0000
   9.250   1.2450   0.01587   0.00891  -0.0326   0.1319   1.0000
   9.500   1.2537   0.01673   0.00967  -0.0299   0.1106   1.0000
   9.750   1.2622   0.01752   0.01039  -0.0271   0.0942   1.0000
  10.000   1.2638   0.01856   0.01130  -0.0233   0.0688   1.0000
  10.250   1.2581   0.01963   0.01228  -0.0183   0.0518   1.0000
  10.500   1.2574   0.02072   0.01334  -0.0147   0.0421   1.0000
  10.750   1.2610   0.02193   0.01456  -0.0122   0.0347   1.0000
  11.000   1.2669   0.02323   0.01587  -0.0105   0.0292   1.0000
  11.250   1.2737   0.02463   0.01730  -0.0091   0.0254   1.0000
  11.500   1.2800   0.02618   0.01888  -0.0080   0.0225   1.0000
  11.750   1.2879   0.02771   0.02046  -0.0072   0.0206   1.0000
  12.000   1.2942   0.02945   0.02225  -0.0064   0.0191   1.0000
  12.250   1.2997   0.03133   0.02419  -0.0058   0.0180   1.0000
  12.500   1.3062   0.03319   0.02613  -0.0053   0.0172   1.0000
  12.750   1.3113   0.03521   0.02822  -0.0049   0.0165   1.0000
  13.000   1.3150   0.03741   0.03049  -0.0045   0.0158   1.0000
  13.250   1.3172   0.03981   0.03295  -0.0041   0.0152   1.0000
  13.500   1.3173   0.04243   0.03565  -0.0038   0.0147   1.0000
  13.750   1.3178   0.04507   0.03837  -0.0036   0.0143   1.0000
  14.000   1.3193   0.04761   0.04100  -0.0035   0.0139   1.0000
  14.250   1.3200   0.05029   0.04377  -0.0034   0.0135   1.0000
  14.500   1.3202   0.05311   0.04667  -0.0034   0.0131   1.0000
  14.750   1.3199   0.05607   0.04971  -0.0036   0.0128   1.0000
  15.000   1.3190   0.05915   0.05287  -0.0038   0.0124   1.0000
  15.250   1.3172   0.06241   0.05622  -0.0041   0.0122   1.0000
  15.500   1.3145   0.06585   0.05973  -0.0046   0.0119   1.0000
  15.750   1.3107   0.06947   0.06344  -0.0051   0.0117   1.0000
  16.000   1.3054   0.07335   0.06740  -0.0057   0.0114   1.0000
  16.250   1.3006   0.07724   0.07137  -0.0064   0.0112   1.0000
  16.500   1.2989   0.08074   0.07496  -0.0071   0.0111   1.0000
  16.750   1.2967   0.08430   0.07862  -0.0078   0.0109   1.0000
  17.000   1.2938   0.08802   0.08243  -0.0086   0.0107   1.0000
  17.250   1.2909   0.09179   0.08627  -0.0095   0.0106   1.0000
  17.500   1.2883   0.09553   0.09010  -0.0104   0.0104   1.0000
  17.750   1.2850   0.09940   0.09407  -0.0114   0.0102   1.0000
  18.000   1.2821   0.10322   0.09797  -0.0125   0.0100   1.0000
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