Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

MRC-20 (mrc-20-il)

MRC-20 - Drela MRC-20


Airfoil mrc-20-il
Details Dat file Parser  
(mrc-20-il) MRC-20
Drela MRC-20
Max thickness 15.6% at 38.2% chord.
Max camber 2.9% at 48% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
MRC-20
   1.000000  0.000000
   0.990961  0.002588
   0.978145  0.006418
   0.961886  0.011643
   0.943404  0.017741
   0.924434  0.023936
   0.905606  0.029914
   0.886922  0.035603
   0.868261  0.041008
   0.849524  0.046152
   0.830665  0.051058
   0.811685  0.055739
   0.792599  0.060205
   0.773430  0.064457
   0.754194  0.068494
   0.734890  0.072321
   0.715518  0.075942
   0.696075  0.079364
   0.676574  0.082591
   0.657016  0.085626
   0.637417  0.088473
   0.617785  0.091131
   0.598131  0.093599
   0.578467  0.095874
   0.558793  0.097953
   0.539118  0.099832
   0.519445  0.101509
   0.499780  0.102977
   0.480130  0.104232
   0.460494  0.105268
   0.440881  0.106079
   0.421287  0.106660
   0.401727  0.107006
   0.382199  0.107109
   0.362715  0.106964
   0.343280  0.106562
   0.323926  0.105898
   0.304704  0.104953
   0.285591  0.103707
   0.266599  0.102146
   0.247741  0.100257
   0.229038  0.098024
   0.210511  0.095430
   0.192189  0.092462
   0.174102  0.089099
   0.156296  0.085327
   0.138816  0.081128
   0.121735  0.076488
   0.105136  0.071397
   0.089126  0.065846
   0.073841  0.059849
   0.059491  0.053453
   0.046356  0.046762
   0.034774  0.039973
   0.025073  0.033383
   0.017390  0.027291
   0.011568  0.021850
   0.007272  0.017027
   0.004172  0.012710
   0.002041  0.008763
   0.000714  0.005099
   0.000081  0.001688
   0.000064 -0.001488
   0.000674 -0.004546
   0.002141 -0.007327
   0.004652 -0.009573
   0.008122 -0.011373
   0.012646 -0.013054
   0.018648 -0.014808
   0.026910 -0.016749
   0.038387 -0.018954
   0.053474 -0.021371
   0.071259 -0.023836
   0.090443 -0.026226
   0.110310 -0.028531
   0.130510 -0.030774
   0.150884 -0.032971
   0.171323 -0.035138
   0.191725 -0.037260
   0.212024 -0.039317
   0.232155 -0.041268
   0.252081 -0.043073
   0.271779 -0.044681
   0.291290 -0.046049
   0.310665 -0.047146
   0.330002 -0.047961
   0.349349 -0.048494
   0.368745 -0.048750
   0.388213 -0.048743
   0.407763 -0.048484
   0.427415 -0.047991
   0.447160 -0.047284
   0.466998 -0.046381
   0.486926 -0.045301
   0.506942 -0.044061
   0.527053 -0.042682
   0.547251 -0.041181
   0.567549 -0.039580
   0.587937 -0.037900
   0.608410 -0.036160
   0.628946 -0.034381
   0.649505 -0.032574
   0.670082 -0.030743
   0.690668 -0.028890
   0.711270 -0.027020
   0.731881 -0.025136
   0.752508 -0.023239
   0.773146 -0.021335
   0.793792 -0.019422
   0.814448 -0.017508
   0.835097 -0.015595
   0.855730 -0.013690
   0.876348 -0.011794
   0.896955 -0.009914
   0.917564 -0.008045
   0.938104 -0.006189
   0.958188 -0.004376
   0.976426 -0.002714
   0.990514 -0.001399
   1.000000 -0.000500
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

GOE 601 AIRFOILPreviewDetails
NACA 65(2)-415 a=0.5PreviewDetails
HQ 3.0/15 AIRFOILPreviewDetails
EPPLER 682 AIRFOILPreviewDetails
NACA 63(2)-615PreviewDetails
AH 82-150 APreviewDetails
AH 93-157PreviewDetails
RONCZ 1082T VOYAGER TIP OUTER AFTPreviewDetails
NACA 65(2)-415PreviewDetails
AH 94-156PreviewDetails

Polars for MRC-20 (mrc-20-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   mrc-20-il50,000923.9 at α=11.75°Mach=0 Ncrit=9Xfoil predictionDetails
   mrc-20-il50,000529.4 at α=9.5°Mach=0 Ncrit=5Xfoil predictionDetails
   mrc-20-il100,000950.8 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   mrc-20-il100,000550.3 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   mrc-20-il200,000973.1 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   mrc-20-il200,000568.4 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   mrc-20-il500,000999.2 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   mrc-20-il500,000586.6 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   mrc-20-il1,000,0009114.5 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   mrc-20-il1,000,0005100.1 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit