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MRC-20 (mrc-20-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MRC-20 (mrc-20-il)
Reynolds number: 100,000
Max Cl/Cd: 50.31 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mrc-20-il-100000-n5.txt
Download as CSV file: xf-mrc-20-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MRC-20                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3848   0.09716   0.09240  -0.0572   0.9874   0.0559
  -9.000  -0.3848   0.09128   0.08653  -0.0633   0.9836   0.0567
  -8.750  -0.3946   0.08549   0.08071  -0.0689   0.9772   0.0570
  -8.500  -0.4076   0.08080   0.07595  -0.0726   0.9707   0.0572
  -8.000  -0.4419   0.06849   0.06298  -0.0740   0.9521   0.0364
  -7.750  -0.4330   0.06480   0.05915  -0.0749   0.9477   0.0358
  -7.500  -0.4315   0.06172   0.05590  -0.0735   0.9406   0.0353
  -7.000  -0.4155   0.05319   0.04650  -0.0719   0.9299   0.0308
  -6.750  -0.4094   0.05087   0.04403  -0.0696   0.9222   0.0304
  -6.500  -0.3906   0.04786   0.04075  -0.0696   0.9182   0.0298
  -6.250  -0.3748   0.04515   0.03772  -0.0686   0.9132   0.0292
  -6.000  -0.3619   0.04275   0.03501  -0.0666   0.9065   0.0288
  -5.750  -0.3375   0.04004   0.03190  -0.0665   0.9029   0.0283
  -5.500  -0.3084   0.03749   0.02892  -0.0671   0.9005   0.0281
  -5.250  -0.2979   0.03594   0.02711  -0.0639   0.8919   0.0281
  -5.000  -0.2689   0.03400   0.02484  -0.0642   0.8884   0.0283
  -4.750  -0.2359   0.03231   0.02286  -0.0652   0.8861   0.0293
  -4.500  -0.2194   0.03124   0.02153  -0.0629   0.8784   0.0305
  -4.250  -0.1897   0.02990   0.02000  -0.0632   0.8744   0.0318
  -4.000  -0.1557   0.02860   0.01865  -0.0644   0.8718   0.0327
  -3.750  -0.1331   0.02769   0.01769  -0.0634   0.8658   0.0335
  -3.500  -0.1080   0.02677   0.01671  -0.0628   0.8603   0.0347
  -3.250  -0.0762   0.02578   0.01565  -0.0635   0.8571   0.0365
  -3.000  -0.0530   0.02506   0.01499  -0.0628   0.8517   0.0392
  -2.750  -0.0325   0.02451   0.01441  -0.0615   0.8447   0.0424
  -2.500  -0.0023   0.02368   0.01350  -0.0619   0.8413   0.0457
  -2.250   0.0169   0.02326   0.01301  -0.0604   0.8338   0.0505
  -2.000   0.0437   0.02267   0.01236  -0.0603   0.8284   0.0600
  -1.500   0.0826   0.01971   0.01138  -0.0581   0.8170   0.5514
  -1.250   0.1059   0.01930   0.01135  -0.0562   0.8121   0.6687
  -1.000   0.1324   0.01902   0.01132  -0.0544   0.8091   0.7507
  -0.750   0.1465   0.01913   0.01148  -0.0511   0.7993   0.7852
  -0.500   0.1807   0.01887   0.01112  -0.0520   0.7953   0.7985
  -0.250   0.2083   0.01875   0.01092  -0.0517   0.7887   0.8116
   0.000   0.2362   0.01863   0.01074  -0.0516   0.7817   0.8258
   0.250   0.2742   0.01833   0.01035  -0.0532   0.7781   0.8405
   0.500   0.2959   0.01838   0.01038  -0.0519   0.7684   0.8579
   0.750   0.3341   0.01815   0.01008  -0.0536   0.7636   0.8742
   1.000   0.3651   0.01813   0.01003  -0.0542   0.7555   0.8920
   1.250   0.4039   0.01799   0.00984  -0.0562   0.7489   0.9086
   1.500   0.4444   0.01788   0.00968  -0.0586   0.7421   0.9246
   1.750   0.4837   0.01784   0.00960  -0.0610   0.7337   0.9404
   2.000   0.5285   0.01774   0.00944  -0.0645   0.7261   0.9531
   2.250   0.5715   0.01768   0.00934  -0.0677   0.7169   0.9657
   2.500   0.6145   0.01765   0.00928  -0.0710   0.7071   0.9775
   2.750   0.6624   0.01749   0.00906  -0.0752   0.6983   0.9861
   3.000   0.7041   0.01754   0.00910  -0.0785   0.6861   0.9970
   3.250   0.7301   0.01752   0.00904  -0.0784   0.6747   1.0000
   3.500   0.7539   0.01746   0.00891  -0.0778   0.6640   1.0000
   3.750   0.7711   0.01753   0.00893  -0.0759   0.6517   1.0000
   4.000   0.7880   0.01764   0.00899  -0.0739   0.6393   1.0000
   4.250   0.8085   0.01772   0.00903  -0.0726   0.6272   1.0000
   4.500   0.8314   0.01781   0.00907  -0.0718   0.6152   1.0000
   4.750   0.8509   0.01795   0.00918  -0.0703   0.6024   1.0000
   5.000   0.8686   0.01815   0.00935  -0.0685   0.5892   1.0000
   5.250   0.8880   0.01835   0.00954  -0.0670   0.5762   1.0000
   5.500   0.9084   0.01855   0.00971  -0.0657   0.5633   1.0000
   5.750   0.9294   0.01877   0.00988  -0.0645   0.5503   1.0000
   6.000   0.9489   0.01902   0.01011  -0.0631   0.5369   1.0000
   6.250   0.9662   0.01931   0.01042  -0.0614   0.5232   1.0000
   6.500   0.9841   0.01961   0.01072  -0.0597   0.5096   1.0000
   6.750   1.0019   0.01993   0.01103  -0.0580   0.4961   1.0000
   7.000   1.0193   0.02026   0.01136  -0.0563   0.4827   1.0000
   7.250   1.0365   0.02062   0.01170  -0.0546   0.4694   1.0000
   7.500   1.0529   0.02100   0.01207  -0.0528   0.4559   1.0000
   7.750   1.0677   0.02143   0.01252  -0.0507   0.4421   1.0000
   8.000   1.0828   0.02188   0.01301  -0.0488   0.4284   1.0000
   8.250   1.0976   0.02237   0.01351  -0.0468   0.4147   1.0000
   8.500   1.1121   0.02288   0.01404  -0.0449   0.4010   1.0000
   8.750   1.1260   0.02343   0.01461  -0.0429   0.3872   1.0000
   9.000   1.1393   0.02403   0.01521  -0.0409   0.3734   1.0000
   9.250   1.1518   0.02466   0.01585  -0.0388   0.3595   1.0000
   9.500   1.1632   0.02536   0.01659  -0.0367   0.3451   1.0000
   9.750   1.1739   0.02610   0.01739  -0.0345   0.3307   1.0000
  10.000   1.1840   0.02691   0.01823  -0.0323   0.3162   1.0000
  10.250   1.1932   0.02778   0.01914  -0.0302   0.3015   1.0000
  10.500   1.2015   0.02873   0.02011  -0.0280   0.2867   1.0000
  10.750   1.2090   0.02977   0.02119  -0.0258   0.2718   1.0000
  11.000   1.2155   0.03090   0.02234  -0.0236   0.2567   1.0000
  11.250   1.2211   0.03214   0.02360  -0.0215   0.2418   1.0000
  11.500   1.2259   0.03349   0.02497  -0.0195   0.2269   1.0000
  11.750   1.2297   0.03496   0.02647  -0.0175   0.2122   1.0000
  12.000   1.2328   0.03656   0.02810  -0.0156   0.1978   1.0000
  12.250   1.2350   0.03829   0.02985  -0.0138   0.1839   1.0000
  12.500   1.2363   0.04017   0.03176  -0.0121   0.1706   1.0000
  12.750   1.2369   0.04220   0.03381  -0.0105   0.1580   1.0000
  13.000   1.2363   0.04441   0.03605  -0.0091   0.1461   1.0000
  13.250   1.2344   0.04685   0.03849  -0.0078   0.1352   1.0000
  13.500   1.2336   0.04932   0.04104  -0.0068   0.1244   1.0000
  13.750   1.2319   0.05196   0.04374  -0.0059   0.1147   1.0000
  14.000   1.2286   0.05486   0.04669  -0.0052   0.1063   1.0000
  14.250   1.2242   0.05799   0.04986  -0.0047   0.0986   1.0000
  14.500   1.2212   0.06110   0.05306  -0.0043   0.0914   1.0000
  14.750   1.2146   0.06469   0.05667  -0.0041   0.0860   1.0000
  15.000   1.2118   0.06796   0.06007  -0.0041   0.0800   1.0000
  15.250   1.2047   0.07183   0.06398  -0.0043   0.0756   1.0000
  15.500   1.2011   0.07537   0.06765  -0.0046   0.0710   1.0000
  15.750   1.1953   0.07925   0.07162  -0.0050   0.0672   1.0000
  16.000   1.1888   0.08327   0.07567  -0.0056   0.0642   1.0000
  16.250   1.1857   0.08694   0.07950  -0.0062   0.0606   1.0000
  16.500   1.1805   0.09097   0.08361  -0.0071   0.0579   1.0000
  16.750   1.1750   0.09498   0.08763  -0.0080   0.0556   1.0000
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