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MRC-16 (mrc-16-il)

MRC-16 - Drela MRC-16


Airfoil mrc-16-il
Details Dat file Parser  
(mrc-16-il) MRC-16
Drela MRC-16
Max thickness 13.9% at 34.6% chord.
Max camber 3% at 40.3% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
MRC-16
   1.000000  0.000094
   0.991277  0.002239
   0.978383  0.005394
   0.961495  0.009502
   0.942722  0.014043
   0.923460  0.018672
   0.904124  0.023279
   0.884777  0.027836
   0.865439  0.032338
   0.846139  0.036765
   0.826872  0.041098
   0.807626  0.045328
   0.788389  0.049446
   0.769156  0.053444
   0.749919  0.057319
   0.730676  0.061064
   0.711424  0.064675
   0.692162  0.068149
   0.672891  0.071481
   0.653614  0.074667
   0.634332  0.077700
   0.615046  0.080576
   0.595758  0.083287
   0.576469  0.085829
   0.557181  0.088195
   0.537895  0.090378
   0.518613  0.092372
   0.499338  0.094170
   0.480072  0.095766
   0.460818  0.097150
   0.441581  0.098317
   0.422364  0.099256
   0.403171  0.099959
   0.384009  0.100417
   0.364883  0.100620
   0.345798  0.100557
   0.326765  0.100218
   0.307789  0.099589
   0.288882  0.098659
   0.270054  0.097414
   0.251320  0.095839
   0.232693  0.093918
   0.214189  0.091635
   0.195832  0.088974
   0.177663  0.085918
   0.159721  0.082441
   0.142048  0.078518
   0.124697  0.074121
   0.107738  0.069228
   0.091267  0.063815
   0.075417  0.057870
   0.060384  0.051409
   0.046469  0.044509
   0.034113  0.037380
   0.023820  0.030402
   0.015858  0.024004
   0.010047  0.018416
   0.005938  0.013612
   0.003100  0.009441
   0.001241  0.005741
   0.000229  0.002385
   0.000020 -0.000686
   0.000637 -0.003750
   0.002243 -0.006780
   0.004901 -0.009635
   0.008672 -0.012328
   0.013780 -0.014970
   0.020701 -0.017673
   0.030110 -0.020492
   0.042534 -0.023359
   0.057734 -0.026082
   0.074795 -0.028497
   0.092878 -0.030561
   0.111508 -0.032300
   0.130458 -0.033757
   0.149615 -0.034971
   0.168915 -0.035976
   0.188320 -0.036795
   0.207806 -0.037449
   0.227355 -0.037955
   0.246954 -0.038326
   0.266592 -0.038573
   0.286264 -0.038706
   0.305967 -0.038731
   0.325693 -0.038659
   0.345440 -0.038493
   0.365203 -0.038241
   0.384982 -0.037905
   0.404777 -0.037492
   0.424585 -0.037005
   0.444405 -0.036449
   0.464236 -0.035829
   0.484073 -0.035146
   0.503909 -0.034403
   0.523742 -0.033600
   0.543572 -0.032735
   0.563403 -0.031810
   0.583237 -0.030825
   0.603072 -0.029782
   0.622908 -0.028683
   0.642745 -0.027528
   0.662581 -0.026319
   0.682422 -0.025056
   0.702270 -0.023742
   0.722128 -0.022379
   0.742002 -0.020973
   0.761893 -0.019529
   0.781797 -0.018053
   0.801710 -0.016550
   0.821623 -0.015022
   0.841528 -0.013468
   0.861433 -0.011884
   0.881356 -0.010274
   0.901305 -0.008646
   0.921240 -0.007020
   0.941068 -0.005414
   0.960396 -0.003858
   0.977782 -0.002457
   0.991041 -0.001383
   1.000000 -0.000651
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Polars for MRC-16 (mrc-16-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   mrc-16-il50,000923.1 at α=12°Mach=0 Ncrit=9Xfoil predictionDetails
   mrc-16-il50,000531.2 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   mrc-16-il100,000950.5 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   mrc-16-il100,000552.5 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   mrc-16-il200,000973.1 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   mrc-16-il200,000571.1 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   mrc-16-il500,0009102.1 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   mrc-16-il500,000594.4 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   mrc-16-il1,000,0009124.1 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   mrc-16-il1,000,0005110.3 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
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