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NACA M27 AIRFOIL (m27-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA M27 AIRFOIL (m27-il)
Reynolds number: 500,000
Max Cl/Cd: 105.54 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m27-il-500000.txt
Download as CSV file: xf-m27-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M27 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.1771   0.09782   0.09427  -0.0156   0.5877   0.0214
  -7.750  -0.1736   0.09506   0.09148  -0.0202   0.5850   0.0216
  -7.500  -0.1705   0.09260   0.08900  -0.0251   0.5824   0.0217
  -7.250  -0.1604   0.08894   0.08534  -0.0283   0.5793   0.0218
  -7.000  -0.1500   0.08510   0.08150  -0.0272   0.5757   0.0219
  -6.750  -0.1385   0.08209   0.07846  -0.0278   0.5723   0.0221
  -6.500  -0.1257   0.07934   0.07565  -0.0293   0.5691   0.0224
  -6.250  -0.1113   0.07663   0.07291  -0.0312   0.5661   0.0227
  -6.000  -0.0954   0.07386   0.07013  -0.0333   0.5630   0.0232
  -5.750  -0.0782   0.07106   0.06728  -0.0355   0.5598   0.0238
  -5.500  -0.0591   0.06820   0.06436  -0.0379   0.5567   0.0248
  -5.250  -0.0233   0.06551   0.06145  -0.0448   0.5539   0.0258
  -5.000  -0.0017   0.06213   0.05795  -0.0468   0.5509   0.0259
  -4.750   0.0108   0.05871   0.05455  -0.0465   0.5479   0.0262
  -4.500   0.0283   0.05615   0.05197  -0.0469   0.5445   0.0264
  -4.250   0.0484   0.05386   0.04962  -0.0477   0.5415   0.0268
  -4.000   0.0704   0.05167   0.04735  -0.0487   0.5385   0.0273
  -3.750   0.0937   0.04957   0.04513  -0.0497   0.5354   0.0281
  -3.500   0.1194   0.04734   0.04283  -0.0508   0.5326   0.0295
  -3.250   0.1612   0.04530   0.04052  -0.0532   0.5295   0.0308
  -3.000   0.1798   0.04195   0.03709  -0.0533   0.5265   0.0311
  -2.750   0.2001   0.03998   0.03505  -0.0534   0.5235   0.0315
  -2.500   0.2226   0.03833   0.03331  -0.0536   0.5205   0.0319
  -2.250   0.2472   0.03673   0.03165  -0.0539   0.5178   0.0326
  -2.000   0.2733   0.03511   0.02995  -0.0542   0.5148   0.0337
  -1.750   0.3116   0.03379   0.02835  -0.0544   0.5118   0.0366
  -1.500   0.3341   0.03093   0.02534  -0.0542   0.5091   0.0372
  -1.250   0.3569   0.02954   0.02387  -0.0543   0.5060   0.0377
  -1.000   0.3817   0.02843   0.02268  -0.0544   0.5031   0.0386
  -0.750   0.4083   0.02725   0.02143  -0.0544   0.5004   0.0400
  -0.500   0.4443   0.02639   0.02026  -0.0539   0.4975   0.0438
  -0.250   0.4661   0.02401   0.01781  -0.0538   0.4948   0.0450
   0.000   0.4918   0.02319   0.01693  -0.0540   0.4919   0.0461
   0.250   0.5187   0.02249   0.01610  -0.0540   0.4888   0.0484
   0.500   0.5490   0.02094   0.01428  -0.0534   0.4862   0.0534
   0.750   0.5754   0.02016   0.01350  -0.0537   0.4834   0.0546
   1.000   0.6028   0.01953   0.01282  -0.0538   0.4805   0.0568
   1.250   0.6346   0.01993   0.01295  -0.0535   0.4777   0.0625
   1.500   0.6593   0.01785   0.01080  -0.0536   0.4751   0.0654
   1.750   0.6869   0.01739   0.01025  -0.0537   0.4721   0.0681
   2.000   0.7172   0.01785   0.01057  -0.0536   0.4694   0.0744
   2.250   0.7485   0.01365   0.00583  -0.0528   0.4670   0.0430
   2.500   0.7760   0.01330   0.00544  -0.0528   0.4642   0.0431
   2.750   0.8031   0.01309   0.00519  -0.0527   0.4616   0.0437
   3.000   0.8288   0.01284   0.00489  -0.0524   0.4589   0.0449
   3.250   0.8551   0.01279   0.00484  -0.0523   0.4561   0.0468
   3.500   0.8821   0.01272   0.00482  -0.0524   0.4534   0.0495
   3.750   0.9090   0.01268   0.00481  -0.0524   0.4505   0.0540
   4.250   0.9627   0.01267   0.00491  -0.0525   0.4453   0.1029
   4.500   0.9895   0.01277   0.00502  -0.0526   0.4426   0.1305
   4.750   1.0160   0.01282   0.00521  -0.0527   0.4400   0.1839
   5.000   1.0675   0.01182   0.00582  -0.0580   0.4368   0.9786
   5.250   1.2022   0.01224   0.00618  -0.0818   0.4320   1.0000
   5.500   1.2275   0.01238   0.00628  -0.0817   0.4295   1.0000
   5.750   1.2526   0.01260   0.00643  -0.0816   0.4268   1.0000
   6.000   1.2775   0.01275   0.00661  -0.0814   0.4244   1.0000
   6.250   1.3023   0.01287   0.00678  -0.0812   0.4217   1.0000
   6.500   1.3268   0.01300   0.00693  -0.0810   0.4185   1.0000
   6.750   1.3509   0.01311   0.00702  -0.0808   0.4144   1.0000
   7.000   1.3746   0.01333   0.00720  -0.0804   0.4102   1.0000
   7.250   1.3983   0.01344   0.00739  -0.0801   0.4067   1.0000
   7.500   1.4216   0.01356   0.00754  -0.0798   0.4020   1.0000
   7.750   1.4443   0.01376   0.00771  -0.0793   0.3974   1.0000
   8.000   1.4667   0.01396   0.00795  -0.0789   0.3932   1.0000
   8.250   1.4891   0.01411   0.00817  -0.0784   0.3886   1.0000
   8.500   1.5103   0.01433   0.00838  -0.0777   0.3833   1.0000
   8.750   1.5309   0.01458   0.00867  -0.0770   0.3777   1.0000
   9.000   1.5506   0.01481   0.00893  -0.0761   0.3696   1.0000
   9.250   1.5689   0.01513   0.00926  -0.0750   0.3623   1.0000
   9.500   1.5849   0.01552   0.00965  -0.0736   0.3526   1.0000
   9.750   1.5983   0.01599   0.01014  -0.0719   0.3397   1.0000
  10.000   1.6026   0.01680   0.01088  -0.0688   0.3222   1.0000
  10.250   1.5953   0.01788   0.01190  -0.0639   0.3048   1.0000
  10.500   1.5757   0.01929   0.01329  -0.0576   0.2930   1.0000
  10.750   1.5597   0.02138   0.01532  -0.0532   0.2749   1.0000
  11.000   1.5414   0.02423   0.01808  -0.0496   0.2526   1.0000
  11.250   1.5199   0.02782   0.02157  -0.0466   0.2288   1.0000
  11.500   1.4934   0.03219   0.02583  -0.0440   0.2038   1.0000
  11.750   1.4643   0.03703   0.03058  -0.0417   0.1792   1.0000
  12.000   1.4363   0.04199   0.03547  -0.0398   0.1568   1.0000
  12.250   1.4086   0.04726   0.04067  -0.0382   0.1340   1.0000
  12.500   1.3813   0.05277   0.04611  -0.0371   0.1107   1.0000
  12.750   1.3543   0.05848   0.05175  -0.0362   0.0852   1.0000
  13.000   1.3283   0.06427   0.05747  -0.0355   0.0606   1.0000
  13.250   1.3031   0.07018   0.06331  -0.0351   0.0349   1.0000
  13.500   1.2907   0.07466   0.06778  -0.0349   0.0253   1.0000
  13.750   1.2866   0.07819   0.07135  -0.0348   0.0225   1.0000
  14.000   1.2850   0.08146   0.07470  -0.0348   0.0214   1.0000
  14.250   1.2836   0.08472   0.07804  -0.0348   0.0206   1.0000
  14.500   1.2803   0.08826   0.08167  -0.0349   0.0198   1.0000
  14.750   1.2771   0.09179   0.08528  -0.0350   0.0191   1.0000
  15.000   1.2716   0.09574   0.08930  -0.0352   0.0184   1.0000
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