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NACA M23 AIRFOIL (m23-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA M23 AIRFOIL (m23-il)
Reynolds number: 200,000
Max Cl/Cd: 75.99 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m23-il-200000-n5.txt
Download as CSV file: xf-m23-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M23 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  -0.3818   0.11191   0.10804   0.0158   0.6743   0.0190
  -8.000  -0.3776   0.10908   0.10519   0.0126   0.6700   0.0191
  -7.750  -0.3736   0.10618   0.10228   0.0096   0.6651   0.0191
  -7.500  -0.3645   0.10270   0.09877   0.0065   0.6602   0.0192
  -7.250  -0.3538   0.09912   0.09514   0.0035   0.6561   0.0192
  -7.000  -0.3415   0.09543   0.09140   0.0004   0.6517   0.0192
  -6.750  -0.3279   0.09150   0.08745  -0.0024   0.6468   0.0192
  -6.500  -0.3229   0.08653   0.08248   0.0006   0.6423   0.0197
  -6.250  -0.3108   0.08322   0.07911  -0.0006   0.6380   0.0202
  -6.000  -0.2960   0.08005   0.07590  -0.0027   0.6330   0.0210
  -5.750  -0.2771   0.07720   0.07297  -0.0054   0.6285   0.0237
  -5.500  -0.2446   0.07494   0.07051  -0.0120   0.6247   0.0252
  -5.250  -0.2211   0.07148   0.06694  -0.0151   0.6199   0.0253
  -5.000  -0.1979   0.06792   0.06326  -0.0175   0.6154   0.0254
  -4.750  -0.1738   0.06444   0.05962  -0.0196   0.6114   0.0255
  -4.250  -0.1445   0.05636   0.05146  -0.0204   0.6029   0.0271
  -4.000  -0.1229   0.05370   0.04869  -0.0214   0.5985   0.0284
  -3.500  -0.0530   0.05030   0.04477  -0.0254   0.5898   0.0348
  -3.250  -0.0254   0.04768   0.04195  -0.0262   0.5855   0.0350
  -3.000  -0.0054   0.04298   0.03708  -0.0268   0.5821   0.0358
  -2.750   0.0142   0.04034   0.03437  -0.0270   0.5781   0.0369
  -2.500   0.0373   0.03848   0.03242  -0.0273   0.5732   0.0391
  -2.250   0.0758   0.03812   0.03168  -0.0279   0.5689   0.0469
  -2.000   0.1047   0.03632   0.02959  -0.0279   0.5655   0.0472
  -1.750   0.1267   0.03261   0.02577  -0.0283   0.5614   0.0484
  -1.500   0.1506   0.03080   0.02389  -0.0285   0.5568   0.0498
  -1.250   0.1763   0.02952   0.02249  -0.0287   0.5528   0.0529
  -1.000   0.2096   0.02846   0.02098  -0.0285   0.5493   0.0609
  -0.750   0.2365   0.02562   0.01799  -0.0283   0.5450   0.0446
  -0.500   0.2648   0.02386   0.01600  -0.0282   0.5409   0.0416
  -0.250   0.2942   0.02202   0.01381  -0.0278   0.5373   0.0395
   0.000   0.3236   0.02041   0.01188  -0.0276   0.5336   0.0386
   0.250   0.3523   0.01952   0.01083  -0.0277   0.5291   0.0397
   0.500   0.3809   0.01873   0.00986  -0.0277   0.5251   0.0412
   0.750   0.4098   0.01773   0.00859  -0.0276   0.5216   0.0403
   1.000   0.4388   0.01693   0.00760  -0.0276   0.5174   0.0396
   1.250   0.4675   0.01631   0.00687  -0.0277   0.5131   0.0392
   1.500   0.4956   0.01583   0.00628  -0.0277   0.5093   0.0391
   2.000   0.5509   0.01513   0.00549  -0.0277   0.5014   0.0399
   2.250   0.5781   0.01487   0.00524  -0.0277   0.4972   0.0406
   2.500   0.6051   0.01468   0.00502  -0.0276   0.4936   0.0418
   2.750   0.6322   0.01456   0.00487  -0.0275   0.4901   0.0431
   3.000   0.6597   0.01449   0.00484  -0.0276   0.4855   0.0457
   3.250   0.6867   0.01442   0.00477  -0.0276   0.4813   0.0493
   3.500   0.7136   0.01440   0.00471  -0.0275   0.4779   0.0516
   3.750   0.7409   0.01443   0.00476  -0.0276   0.4742   0.0555
   4.000   0.7684   0.01447   0.00487  -0.0277   0.4697   0.0705
   5.000   0.9383   0.01373   0.00587  -0.0416   0.4518   1.0000
   5.250   0.9638   0.01390   0.00602  -0.0413   0.4482   1.0000
   5.500   0.9894   0.01409   0.00625  -0.0412   0.4443   1.0000
   5.750   1.0150   0.01428   0.00651  -0.0411   0.4400   1.0000
   6.000   1.0402   0.01443   0.00669  -0.0408   0.4346   1.0000
   6.250   1.0654   0.01454   0.00685  -0.0406   0.4235   1.0000
   6.500   1.0903   0.01466   0.00698  -0.0404   0.4112   1.0000
   6.750   1.1150   0.01482   0.00717  -0.0401   0.3988   1.0000
   7.000   1.1395   0.01503   0.00743  -0.0399   0.3857   1.0000
   7.250   1.1634   0.01531   0.00771  -0.0397   0.3657   1.0000
   7.500   1.1859   0.01576   0.00808  -0.0394   0.3342   1.0000
   7.750   1.2033   0.01693   0.00888  -0.0390   0.2657   1.0000
   8.000   1.1887   0.02163   0.01231  -0.0369   0.0761   1.0000
   8.250   1.1859   0.02408   0.01452  -0.0347   0.0243   1.0000
   8.500   1.1945   0.02534   0.01586  -0.0332   0.0208   1.0000
   8.750   1.1992   0.02679   0.01746  -0.0316   0.0195   1.0000
   9.000   1.1999   0.02850   0.01929  -0.0298   0.0183   1.0000
   9.250   1.2014   0.03047   0.02139  -0.0286   0.0170   1.0000
   9.500   1.2021   0.03273   0.02377  -0.0277   0.0159   1.0000
   9.750   1.2015   0.03524   0.02642  -0.0269   0.0151   1.0000
  10.000   1.1991   0.03804   0.02937  -0.0263   0.0146   1.0000
  10.250   1.1947   0.04114   0.03262  -0.0258   0.0141   1.0000
  10.500   1.1879   0.04456   0.03622  -0.0254   0.0138   1.0000
  10.750   1.1804   0.04811   0.03988  -0.0250   0.0135   1.0000
  11.000   1.1777   0.05117   0.04305  -0.0247   0.0133   1.0000
  11.250   1.1754   0.05419   0.04616  -0.0245   0.0131   1.0000
  11.500   1.1739   0.05716   0.04924  -0.0243   0.0127   1.0000
  11.750   1.1733   0.06011   0.05227  -0.0241   0.0122   1.0000
  12.000   1.1732   0.06304   0.05528  -0.0240   0.0117   1.0000
  12.250   1.1734   0.06595   0.05826  -0.0238   0.0112   1.0000
  12.500   1.1742   0.06872   0.06110  -0.0235   0.0109   1.0000
  12.750   1.1763   0.07129   0.06373  -0.0231   0.0106   1.0000
  13.000   1.1800   0.07362   0.06610  -0.0226   0.0104   1.0000
  13.250   1.1851   0.07569   0.06825  -0.0219   0.0101   1.0000
  13.500   1.1916   0.07750   0.07010  -0.0209   0.0098   1.0000
  13.750   1.1998   0.07901   0.07164  -0.0197   0.0096   1.0000
  14.000   1.2107   0.08005   0.07269  -0.0180   0.0094   1.0000
  14.250   1.2301   0.07966   0.07226  -0.0143   0.0089   1.0000
  14.500   1.2320   0.08269   0.07549  -0.0147   0.0087   1.0000
  14.750   1.2344   0.08566   0.07866  -0.0151   0.0083   1.0000
  15.000   1.2381   0.08845   0.08163  -0.0151   0.0080   1.0000
  15.250   1.2416   0.09125   0.08462  -0.0148   0.0078   1.0000
  15.500   1.2435   0.09437   0.08794  -0.0148   0.0077   1.0000
  15.750   1.2433   0.09784   0.09161  -0.0150   0.0076   1.0000
  16.000   1.2410   0.10172   0.09569  -0.0156   0.0075   1.0000
  16.250   1.2370   0.10597   0.10015  -0.0165   0.0075   1.0000
  16.500   1.2312   0.11061   0.10499  -0.0178   0.0074   1.0000
  16.750   1.2238   0.11562   0.11020  -0.0194   0.0074   1.0000
  17.000   1.2152   0.12096   0.11574  -0.0215   0.0074   1.0000
  17.250   1.2057   0.12665   0.12163  -0.0239   0.0074   1.0000
  17.500   1.1954   0.13269   0.12786  -0.0267   0.0074   1.0000
  17.750   1.1843   0.13910   0.13447  -0.0299   0.0074   1.0000
  18.000   1.1726   0.14591   0.14146  -0.0336   0.0074   1.0000
  18.250   1.1604   0.15310   0.14882  -0.0377   0.0075   1.0000
  18.500   1.1479   0.16075   0.15663  -0.0422   0.0075   1.0000
  18.750   1.1351   0.16888   0.16492  -0.0472   0.0076   1.0000
  19.000   1.1223   0.17754   0.17373  -0.0526   0.0077   1.0000
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