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NACA M9 AIRFOIL (m9-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA M9 AIRFOIL (m9-il)
Reynolds number: 1,000,000
Max Cl/Cd: 99.52 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m9-il-1000000.txt
Download as CSV file: xf-m9-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M9 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2528   0.10615   0.10373   0.0068   0.6664   0.0163
  -9.500  -0.2463   0.10257   0.10014   0.0054   0.6607   0.0169
  -9.000  -0.5351   0.03624   0.03302  -0.0510   0.6959   0.0148
  -8.750  -0.5201   0.02785   0.02413  -0.0573   0.6908   0.0152
  -8.500  -0.4978   0.02428   0.02030  -0.0593   0.6852   0.0157
  -8.250  -0.4731   0.02218   0.01803  -0.0601   0.6788   0.0162
  -8.000  -0.4478   0.02055   0.01623  -0.0605   0.6721   0.0167
  -7.750  -0.4221   0.01900   0.01451  -0.0608   0.6659   0.0173
  -7.500  -0.3959   0.01774   0.01307  -0.0608   0.6588   0.0178
  -7.250  -0.3693   0.01671   0.01187  -0.0607   0.6517   0.0182
  -7.000  -0.3435   0.01535   0.01037  -0.0606   0.6436   0.0192
  -6.750  -0.3163   0.01465   0.00956  -0.0603   0.6348   0.0200
  -6.500  -0.2889   0.01400   0.00882  -0.0601   0.6248   0.0209
  -6.250  -0.2613   0.01346   0.00815  -0.0598   0.6147   0.0217
  -6.000  -0.2343   0.01275   0.00732  -0.0594   0.6033   0.0229
  -5.750  -0.2065   0.01237   0.00687  -0.0591   0.5911   0.0241
  -5.500  -0.1785   0.01209   0.00650  -0.0587   0.5787   0.0254
  -5.250  -0.1508   0.01174   0.00603  -0.0583   0.5659   0.0266
  -4.750  -0.0951   0.01120   0.00533  -0.0576   0.5403   0.0296
  -4.500  -0.0669   0.01104   0.00508  -0.0573   0.5290   0.0308
  -4.250  -0.0392   0.01071   0.00466  -0.0569   0.5183   0.0328
  -4.000  -0.0110   0.01056   0.00448  -0.0565   0.5091   0.0345
  -3.750   0.0173   0.01045   0.00429  -0.0562   0.4999   0.0361
  -3.500   0.0453   0.01021   0.00396  -0.0558   0.4910   0.0378
  -3.250   0.0734   0.01005   0.00377  -0.0555   0.4821   0.0399
  -3.000   0.1017   0.00995   0.00362  -0.0552   0.4739   0.0418
  -2.750   0.1301   0.00989   0.00348  -0.0548   0.4663   0.0432
  -2.500   0.1582   0.00964   0.00320  -0.0545   0.4597   0.0462
  -2.250   0.1864   0.00956   0.00307  -0.0542   0.4531   0.0485
  -2.000   0.2148   0.00948   0.00296  -0.0539   0.4476   0.0506
  -1.750   0.2431   0.00931   0.00276  -0.0535   0.4417   0.0542
  -1.500   0.2713   0.00925   0.00265  -0.0532   0.4352   0.0576
  -1.250   0.2997   0.00918   0.00257  -0.0529   0.4305   0.0604
  -1.000   0.3280   0.00904   0.00243  -0.0526   0.4258   0.0665
  -0.750   0.3563   0.00901   0.00237  -0.0523   0.4211   0.0705
  -0.500   0.3844   0.00893   0.00230  -0.0520   0.4167   0.0782
  -0.250   0.4129   0.00890   0.00227  -0.0518   0.4126   0.0830
   0.000   0.4410   0.00880   0.00219  -0.0515   0.4078   0.0918
   0.250   0.4691   0.00883   0.00217  -0.0512   0.4022   0.0966
   0.500   0.4972   0.00873   0.00210  -0.0509   0.3982   0.1052
   0.750   0.5253   0.00870   0.00205  -0.0506   0.3942   0.1108
   1.000   0.5532   0.00865   0.00200  -0.0503   0.3899   0.1198
   1.500   0.6095   0.00873   0.00228  -0.0498   0.3816   0.2086
   1.750   0.6389   0.00905   0.00258  -0.0497   0.3771   0.2190
   2.000   0.6676   0.00940   0.00290  -0.0495   0.3719   0.2233
   2.250   0.6960   0.00971   0.00320  -0.0493   0.3670   0.2269
   2.500   0.7244   0.00988   0.00338  -0.0490   0.3625   0.2305
   2.750   0.7525   0.01007   0.00352  -0.0488   0.3572   0.2336
   3.000   0.7802   0.01016   0.00362  -0.0486   0.3516   0.2358
   3.250   0.8083   0.01027   0.00377  -0.0484   0.3465   0.2381
   3.500   0.8360   0.01042   0.00390  -0.0482   0.3395   0.2413
   3.750   0.8638   0.01050   0.00396  -0.0480   0.3328   0.2429
   4.000   0.8915   0.01061   0.00403  -0.0478   0.3238   0.2440
   4.250   0.9191   0.01077   0.00415  -0.0476   0.3137   0.2450
   4.500   0.9461   0.01084   0.00415  -0.0474   0.2996   0.2460
   4.750   0.9722   0.01097   0.00419  -0.0471   0.2757   0.2480
   5.250   1.0232   0.01170   0.00469  -0.0465   0.2286   0.2515
   5.500   1.0496   0.01188   0.00485  -0.0463   0.2211   0.2524
   5.750   1.0757   0.01209   0.00502  -0.0460   0.2134   0.2526
   6.000   1.1023   0.01224   0.00517  -0.0457   0.2094   0.2541
   6.250   1.1288   0.01247   0.00540  -0.0455   0.2054   0.2561
   6.500   1.1547   0.01271   0.00562  -0.0452   0.2010   0.2567
   6.750   1.1807   0.01285   0.00577  -0.0449   0.1976   0.2564
   7.000   1.2072   0.01292   0.00588  -0.0447   0.1955   0.2563
   7.250   1.2333   0.01304   0.00603  -0.0444   0.1927   0.2562
   7.500   1.2590   0.01320   0.00620  -0.0441   0.1899   0.2561
   7.750   1.2842   0.01341   0.00641  -0.0438   0.1869   0.2560
   8.000   1.3088   0.01367   0.00670  -0.0434   0.1834   0.2560
   8.250   1.3346   0.01380   0.00687  -0.0431   0.1820   0.2559
   8.500   1.3604   0.01390   0.00702  -0.0428   0.1799   0.2559
   8.750   1.3856   0.01406   0.00721  -0.0425   0.1769   0.2559
   9.000   1.4101   0.01428   0.00744  -0.0421   0.1734   0.2559
   9.250   1.4333   0.01461   0.00776  -0.0416   0.1686   0.2559
   9.500   1.4584   0.01474   0.00795  -0.0413   0.1667   0.2559
   9.750   1.4830   0.01491   0.00817  -0.0409   0.1642   0.2559
  10.000   1.5068   0.01514   0.00842  -0.0404   0.1608   0.2559
  10.250   1.5295   0.01545   0.00874  -0.0399   0.1565   0.2560
  10.500   1.5522   0.01574   0.00907  -0.0393   0.1532   0.2561
  10.750   1.5754   0.01597   0.00933  -0.0388   0.1489   0.2562
  11.000   1.5961   0.01638   0.00972  -0.0381   0.1423   0.2563
  11.250   1.6172   0.01673   0.01009  -0.0373   0.1365   0.2565
  11.500   1.6349   0.01728   0.01062  -0.0363   0.1269   0.2568
  11.750   1.6480   0.01808   0.01133  -0.0347   0.1107   0.2569
  12.000   1.6300   0.02020   0.01318  -0.0294   0.0750   0.2569
  12.250   1.6201   0.02181   0.01477  -0.0255   0.0660   0.2570
  12.500   1.6163   0.02356   0.01655  -0.0233   0.0599   0.2571
  12.750   1.6173   0.02528   0.01831  -0.0219   0.0568   0.2572
  13.000   1.6169   0.02731   0.02037  -0.0208   0.0533   0.2574
  13.250   1.6202   0.02911   0.02224  -0.0200   0.0502   0.2579
  13.500   1.6183   0.03143   0.02460  -0.0192   0.0465   0.2582
  13.750   1.6143   0.03402   0.02722  -0.0186   0.0414   0.2589
  14.000   1.6056   0.03724   0.03044  -0.0182   0.0345   0.2588
  14.500   1.5661   0.04665   0.03985  -0.0187   0.0168   0.2589
  14.750   1.5563   0.05057   0.04386  -0.0192   0.0155   0.2591
  15.000   1.5466   0.05465   0.04802  -0.0199   0.0145   0.2593
  15.250   1.5385   0.05874   0.05221  -0.0208   0.0137   0.2593
  15.500   1.5327   0.06263   0.05620  -0.0218   0.0133   0.2595
  15.750   1.5238   0.06704   0.06072  -0.0231   0.0128   0.2600
  16.000   1.5147   0.07160   0.06537  -0.0245   0.0125   0.2601
  16.250   1.5062   0.07618   0.07005  -0.0259   0.0123   0.2602
  16.500   1.4936   0.08152   0.07550  -0.0279   0.0119   0.2606
  16.750   1.4795   0.08724   0.08133  -0.0300   0.0115   0.2610
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