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NACA M18 (nacam18-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA M18 (nacam18-il)
Reynolds number: 200,000
Max Cl/Cd: 72.34 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nacam18-il-200000-n5.txt
Download as CSV file: xf-nacam18-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M18                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4035   0.09381   0.09031  -0.0241   0.8726   0.0424
  -8.500  -0.3943   0.09181   0.08825  -0.0225   0.8541   0.0431
  -8.250  -0.3893   0.08913   0.08551  -0.0229   0.8376   0.0439
  -8.000  -0.3872   0.08585   0.08218  -0.0247   0.8223   0.0448
  -7.750  -0.3883   0.08206   0.07833  -0.0277   0.8082   0.0455
  -7.500  -0.3897   0.07837   0.07455  -0.0298   0.7957   0.0459
  -7.250  -0.3869   0.07433   0.07042  -0.0323   0.7843   0.0463
  -7.000  -0.3822   0.07014   0.06611  -0.0346   0.7734   0.0461
  -6.000  -0.3676   0.04019   0.03456  -0.0401   0.7408   0.0346
  -5.750  -0.3545   0.03630   0.03026  -0.0390   0.7329   0.0345
  -5.500  -0.3392   0.03278   0.02629  -0.0378   0.7245   0.0346
  -5.250  -0.3220   0.02991   0.02297  -0.0365   0.7171   0.0349
  -5.000  -0.3007   0.02825   0.02112  -0.0359   0.7087   0.0355
  -4.500  -0.2549   0.02526   0.01760  -0.0345   0.6940   0.0363
  -4.250  -0.2312   0.02362   0.01560  -0.0337   0.6872   0.0365
  -4.000  -0.2061   0.02229   0.01399  -0.0332   0.6805   0.0367
  -3.750  -0.1802   0.02118   0.01261  -0.0327   0.6737   0.0370
  -3.500  -0.1539   0.02023   0.01143  -0.0323   0.6678   0.0374
  -3.250  -0.1269   0.01937   0.01040  -0.0321   0.6611   0.0379
  -3.000  -0.0998   0.01863   0.00947  -0.0318   0.6551   0.0384
  -2.750  -0.0725   0.01796   0.00866  -0.0316   0.6492   0.0390
  -2.500  -0.0450   0.01742   0.00802  -0.0314   0.6430   0.0400
  -2.250  -0.0177   0.01696   0.00742  -0.0312   0.6375   0.0410
  -2.000   0.0098   0.01651   0.00689  -0.0310   0.6315   0.0417
  -1.750   0.0366   0.01593   0.00630  -0.0308   0.6256   0.0424
  -1.500   0.0632   0.01552   0.00584  -0.0305   0.6206   0.0433
  -1.250   0.0901   0.01518   0.00551  -0.0303   0.6146   0.0443
  -1.000   0.1170   0.01489   0.00520  -0.0301   0.6087   0.0456
  -0.750   0.1437   0.01466   0.00490  -0.0298   0.6038   0.0471
  -0.500   0.1708   0.01444   0.00467  -0.0297   0.5979   0.0490
  -0.250   0.1975   0.01423   0.00447  -0.0294   0.5920   0.0522
   0.250   0.2513   0.01388   0.00416  -0.0291   0.5809   0.0667
   0.500   0.2778   0.01369   0.00403  -0.0288   0.5752   0.0881
   0.750   0.3040   0.01351   0.00394  -0.0286   0.5702   0.1268
   1.000   0.3303   0.01331   0.00392  -0.0284   0.5638   0.1774
   1.250   0.3522   0.01269   0.00387  -0.0276   0.5583   0.3548
   1.500   0.4314   0.01185   0.00465  -0.0371   0.5512   0.9682
   1.750   0.4954   0.01209   0.00479  -0.0447   0.5434   0.9875
   2.000   0.5585   0.01218   0.00476  -0.0524   0.5365   1.0000
   2.250   0.5844   0.01222   0.00475  -0.0523   0.5298   1.0000
   2.500   0.6101   0.01227   0.00472  -0.0520   0.5240   1.0000
   2.750   0.6359   0.01232   0.00475  -0.0519   0.5175   1.0000
   3.000   0.6615   0.01238   0.00477  -0.0516   0.5109   1.0000
   3.250   0.6869   0.01246   0.00479  -0.0514   0.5049   1.0000
   3.500   0.7122   0.01254   0.00486  -0.0511   0.4979   1.0000
   3.750   0.7372   0.01264   0.00489  -0.0508   0.4919   1.0000
   4.000   0.7623   0.01273   0.00500  -0.0505   0.4849   1.0000
   4.250   0.7871   0.01285   0.00509  -0.0502   0.4785   1.0000
   4.500   0.8119   0.01297   0.00520  -0.0498   0.4723   1.0000
   4.750   0.8365   0.01310   0.00533  -0.0495   0.4657   1.0000
   5.000   0.8608   0.01325   0.00545  -0.0491   0.4600   1.0000
   5.250   0.8853   0.01340   0.00564  -0.0487   0.4533   1.0000
   5.500   0.9095   0.01356   0.00580  -0.0483   0.4475   1.0000
   5.750   0.9335   0.01374   0.00600  -0.0479   0.4419   1.0000
   6.000   0.9574   0.01392   0.00622  -0.0475   0.4355   1.0000
   6.250   0.9809   0.01413   0.00640  -0.0469   0.4294   1.0000
   6.500   1.0044   0.01432   0.00667  -0.0465   0.4218   1.0000
   6.750   1.0274   0.01454   0.00688  -0.0459   0.4150   1.0000
   7.000   1.0505   0.01476   0.00716  -0.0453   0.4082   1.0000
   7.250   1.0732   0.01500   0.00745  -0.0447   0.4015   1.0000
   7.500   1.0956   0.01525   0.00773  -0.0441   0.3944   1.0000
   7.750   1.1175   0.01550   0.00803  -0.0434   0.3859   1.0000
   8.000   1.1393   0.01577   0.00835  -0.0427   0.3786   1.0000
   8.250   1.1611   0.01605   0.00871  -0.0420   0.3718   1.0000
   8.500   1.1820   0.01635   0.00905  -0.0411   0.3639   1.0000
   8.750   1.2010   0.01667   0.00939  -0.0400   0.3500   1.0000
   9.000   1.2181   0.01705   0.00975  -0.0386   0.3290   1.0000
   9.250   1.2328   0.01756   0.01019  -0.0369   0.3064   1.0000
   9.500   1.2477   0.01809   0.01070  -0.0352   0.2862   1.0000
   9.750   1.2602   0.01872   0.01128  -0.0332   0.2651   1.0000
  10.000   1.2697   0.01948   0.01196  -0.0308   0.2433   1.0000
  10.250   1.2768   0.02033   0.01274  -0.0282   0.2198   1.0000
  10.500   1.2788   0.02139   0.01370  -0.0249   0.1930   1.0000
  10.750   1.2719   0.02271   0.01488  -0.0204   0.1629   1.0000
  11.000   1.2619   0.02461   0.01659  -0.0166   0.1336   1.0000
  11.250   1.2560   0.02668   0.01856  -0.0141   0.1130   1.0000
  11.500   1.2528   0.02884   0.02067  -0.0123   0.0943   1.0000
  11.750   1.2473   0.03139   0.02314  -0.0108   0.0707   1.0000
  12.000   1.2408   0.03423   0.02589  -0.0096   0.0554   1.0000
  12.250   1.2368   0.03698   0.02863  -0.0088   0.0465   1.0000
  12.500   1.2333   0.03980   0.03148  -0.0082   0.0405   1.0000
  12.750   1.2323   0.04245   0.03421  -0.0077   0.0363   1.0000
  13.000   1.2288   0.04542   0.03723  -0.0074   0.0334   1.0000
  13.250   1.2282   0.04814   0.04005  -0.0072   0.0310   1.0000
  13.500   1.2255   0.05112   0.04311  -0.0070   0.0292   1.0000
  13.750   1.2209   0.05441   0.04647  -0.0070   0.0278   1.0000
  14.000   1.2188   0.05752   0.04968  -0.0071   0.0267   1.0000
  14.250   1.2167   0.06072   0.05299  -0.0073   0.0257   1.0000
  14.500   1.2141   0.06407   0.05644  -0.0077   0.0247   1.0000
  14.750   1.2108   0.06756   0.06004  -0.0081   0.0239   1.0000
  15.000   1.2064   0.07128   0.06383  -0.0087   0.0232   1.0000
  15.250   1.2004   0.07528   0.06790  -0.0093   0.0226   1.0000
  15.500   1.1990   0.07871   0.07144  -0.0099   0.0219   1.0000
  15.750   1.1970   0.08225   0.07509  -0.0106   0.0212   1.0000
  16.000   1.1949   0.08586   0.07880  -0.0114   0.0206   1.0000
  16.250   1.1929   0.08947   0.08250  -0.0122   0.0200   1.0000
  16.500   1.1908   0.09313   0.08623  -0.0130   0.0195   1.0000
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