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NACA M20 AIRFOIL (m20-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA M20 AIRFOIL (m20-il)
Reynolds number: 200,000
Max Cl/Cd: 77.95 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m20-il-200000-n5.txt
Download as CSV file: xf-m20-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M20 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  -0.3436   0.10732   0.10357  -0.0025   0.7453   0.0221
  -8.000  -0.3388   0.10455   0.10078  -0.0056   0.7378   0.0222
  -7.750  -0.3350   0.10186   0.09807  -0.0093   0.7301   0.0223
  -7.500  -0.3254   0.09861   0.09477  -0.0138   0.7234   0.0224
  -7.250  -0.3135   0.09489   0.09100  -0.0172   0.7165   0.0224
  -7.000  -0.3002   0.09108   0.08711  -0.0204   0.7105   0.0225
  -6.750  -0.2887   0.08650   0.08251  -0.0226   0.7040   0.0226
  -6.500  -0.2825   0.08231   0.07831  -0.0198   0.6978   0.0232
  -6.250  -0.2698   0.07922   0.07516  -0.0208   0.6915   0.0239
  -6.000  -0.2544   0.07646   0.07234  -0.0226   0.6850   0.0257
  -5.750  -0.2219   0.07443   0.07014  -0.0303   0.6791   0.0298
  -5.500  -0.1967   0.07115   0.06673  -0.0348   0.6728   0.0301
  -5.250  -0.1734   0.06767   0.06311  -0.0377   0.6674   0.0302
  -5.000  -0.1493   0.06429   0.05959  -0.0403   0.6616   0.0303
  -4.750  -0.1315   0.05894   0.05414  -0.0425   0.6562   0.0309
  -4.250  -0.0982   0.05281   0.04788  -0.0432   0.6446   0.0328
  -4.000  -0.0754   0.05030   0.04526  -0.0444   0.6390   0.0344
  -3.750  -0.0497   0.04792   0.04273  -0.0459   0.6336   0.0373
  -3.500  -0.0041   0.04685   0.04124  -0.0492   0.6275   0.0419
  -3.250   0.0227   0.04421   0.03837  -0.0500   0.6223   0.0420
  -3.000   0.0458   0.03999   0.03396  -0.0510   0.6170   0.0426
  -2.750   0.0655   0.03731   0.03124  -0.0514   0.6113   0.0438
  -2.500   0.0877   0.03574   0.02959  -0.0516   0.6063   0.0461
  -2.250   0.1150   0.03410   0.02781  -0.0521   0.6002   0.0497
  -1.750   0.1776   0.02886   0.02182  -0.0525   0.5904   0.0408
  -1.500   0.2045   0.02687   0.01966  -0.0527   0.5846   0.0398
  -1.250   0.2335   0.02515   0.01764  -0.0527   0.5796   0.0405
  -1.000   0.2618   0.02358   0.01578  -0.0526   0.5748   0.0407
  -0.750   0.2897   0.02198   0.01396  -0.0527   0.5690   0.0398
  -0.500   0.3179   0.02055   0.01226  -0.0526   0.5639   0.0391
  -0.250   0.3464   0.01926   0.01069  -0.0525   0.5591   0.0387
   0.000   0.3751   0.01813   0.00932  -0.0524   0.5538   0.0386
   0.250   0.4035   0.01723   0.00817  -0.0524   0.5490   0.0388
   0.500   0.4318   0.01652   0.00726  -0.0523   0.5441   0.0393
   0.750   0.4600   0.01595   0.00656  -0.0523   0.5385   0.0399
   1.000   0.4878   0.01565   0.00614  -0.0523   0.5338   0.0414
   1.250   0.5156   0.01530   0.00570  -0.0523   0.5292   0.0423
   1.500   0.5432   0.01486   0.00525  -0.0522   0.5241   0.0425
   1.750   0.5703   0.01452   0.00486  -0.0521   0.5194   0.0429
   2.000   0.5973   0.01425   0.00458  -0.0520   0.5149   0.0434
   2.250   0.6244   0.01406   0.00441  -0.0520   0.5098   0.0444
   2.500   0.6516   0.01395   0.00429  -0.0519   0.5055   0.0459
   2.750   0.6787   0.01390   0.00421  -0.0519   0.5015   0.0481
   3.000   0.7061   0.01387   0.00420  -0.0519   0.4965   0.0517
   3.250   0.7332   0.01385   0.00422  -0.0518   0.4918   0.0606
   3.500   0.7600   0.01381   0.00429  -0.0518   0.4881   0.1179
   4.000   0.8451   0.01257   0.00471  -0.0587   0.4782   1.0000
   4.250   0.8709   0.01273   0.00482  -0.0584   0.4743   1.0000
   4.500   0.8969   0.01291   0.00498  -0.0582   0.4703   1.0000
   4.750   0.9228   0.01309   0.00520  -0.0580   0.4660   1.0000
   5.000   0.9487   0.01327   0.00538  -0.0578   0.4619   1.0000
   5.250   0.9744   0.01347   0.00554  -0.0575   0.4580   1.0000
   5.500   1.0002   0.01365   0.00582  -0.0574   0.4527   1.0000
   5.750   1.0259   0.01384   0.00606  -0.0572   0.4478   1.0000
   6.000   1.0515   0.01406   0.00626  -0.0569   0.4434   1.0000
   6.250   1.0769   0.01422   0.00652  -0.0567   0.4347   1.0000
   6.500   1.1017   0.01434   0.00668  -0.0564   0.4203   1.0000
   6.750   1.1260   0.01451   0.00684  -0.0560   0.4032   1.0000
   7.000   1.1498   0.01475   0.00706  -0.0556   0.3839   1.0000
   7.250   1.1729   0.01509   0.00736  -0.0552   0.3562   1.0000
   7.500   1.1926   0.01577   0.00785  -0.0544   0.3024   1.0000
   7.750   1.1952   0.01834   0.00953  -0.0523   0.1710   1.0000
   8.000   1.1873   0.02164   0.01208  -0.0492   0.0397   1.0000
   8.250   1.1974   0.02300   0.01341  -0.0474   0.0281   1.0000
   8.500   1.2108   0.02398   0.01453  -0.0460   0.0246   1.0000
   8.750   1.2201   0.02519   0.01586  -0.0443   0.0220   1.0000
   9.000   1.2226   0.02670   0.01753  -0.0420   0.0205   1.0000
   9.250   1.2220   0.02879   0.01980  -0.0403   0.0194   1.0000
   9.500   1.2270   0.03066   0.02180  -0.0393   0.0187   1.0000
   9.750   1.2312   0.03274   0.02401  -0.0386   0.0179   1.0000
  10.000   1.2339   0.03505   0.02645  -0.0380   0.0169   1.0000
  10.250   1.2350   0.03760   0.02912  -0.0375   0.0160   1.0000
  10.500   1.2339   0.04043   0.03207  -0.0370   0.0155   1.0000
  10.750   1.2317   0.04341   0.03516  -0.0366   0.0150   1.0000
  11.000   1.2289   0.04648   0.03832  -0.0362   0.0147   1.0000
  11.250   1.2258   0.04959   0.04151  -0.0358   0.0143   1.0000
  11.500   1.2225   0.05270   0.04472  -0.0353   0.0139   1.0000
  11.750   1.2195   0.05574   0.04783  -0.0347   0.0136   1.0000
  12.000   1.2163   0.05867   0.05081  -0.0339   0.0132   1.0000
  12.250   1.2152   0.06119   0.05333  -0.0324   0.0127   1.0000
  12.500   1.2214   0.06332   0.05558  -0.0320   0.0123   1.0000
  12.750   1.2275   0.06546   0.05782  -0.0316   0.0117   1.0000
  13.000   1.2340   0.06743   0.05987  -0.0307   0.0113   1.0000
  13.250   1.2418   0.06921   0.06171  -0.0296   0.0109   1.0000
  13.500   1.2502   0.07091   0.06350  -0.0284   0.0106   1.0000
  13.750   1.2587   0.07269   0.06539  -0.0273   0.0103   1.0000
  14.000   1.2669   0.07457   0.06738  -0.0262   0.0101   1.0000
  14.250   1.2746   0.07662   0.06955  -0.0253   0.0098   1.0000
  14.500   1.2807   0.07893   0.07199  -0.0246   0.0096   1.0000
  14.750   1.2847   0.08156   0.07475  -0.0242   0.0094   1.0000
  15.000   1.2874   0.08438   0.07768  -0.0241   0.0092   1.0000
  15.250   1.2901   0.08724   0.08062  -0.0238   0.0089   1.0000
  15.500   1.2894   0.09078   0.08433  -0.0235   0.0086   1.0000
  15.750   1.2829   0.09517   0.08897  -0.0247   0.0085   1.0000
  16.000   1.2762   0.09976   0.09380  -0.0260   0.0083   1.0000
  16.250   1.2690   0.10457   0.09884  -0.0273   0.0082   1.0000
  16.500   1.2609   0.10964   0.10413  -0.0289   0.0081   1.0000
  16.750   1.2515   0.11504   0.10975  -0.0309   0.0081   1.0000
  17.000   1.2409   0.12083   0.11575  -0.0332   0.0080   1.0000
  17.250   1.2295   0.12696   0.12208  -0.0360   0.0080   1.0000
  17.500   1.2175   0.13347   0.12878  -0.0393   0.0080   1.0000
  17.750   1.2051   0.14032   0.13582  -0.0430   0.0080   1.0000
  18.000   1.1923   0.14756   0.14324  -0.0471   0.0080   1.0000
  18.250   1.1793   0.15519   0.15104  -0.0517   0.0080   1.0000
  18.500   1.1665   0.16318   0.15919  -0.0566   0.0081   1.0000
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