cr001sm (cr001sm-il)
cr001sm - Cody Robertson CR 001 R/C hand-launch low Reynolds number airfoil (smoothed)
| Details | Dat file | Parser | |
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(cr001sm-il) cr001sm Cody Robertson CR 001 R/C hand-launch low Reynolds number airfoil (smoothed) Max thickness 7.3% at 27.1% chord. Max camber 4.1% at 45.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
cr001sm
1.00000 -0.00001
0.99754 0.00091
0.99070 0.00289
0.98037 0.00531
0.96698 0.00833
0.95044 0.01199
0.93064 0.01619
0.90775 0.02074
0.88202 0.02558
0.85370 0.03061
0.82309 0.03573
0.79048 0.04085
0.75616 0.04586
0.72043 0.05066
0.68359 0.05518
0.64594 0.05935
0.60778 0.06310
0.56937 0.06639
0.53099 0.06918
0.49265 0.07145
0.45435 0.07317
0.41638 0.07429
0.37887 0.07477
0.34204 0.07456
0.30609 0.07364
0.27120 0.07200
0.23760 0.06968
0.20549 0.06673
0.17504 0.06318
0.14648 0.05904
0.11999 0.05431
0.09576 0.04900
0.07395 0.04314
0.05468 0.03682
0.03811 0.03018
0.02433 0.02336
0.01338 0.01648
0.00548 0.00980
0.00098 0.00373
0.00000 -0.00008
0.00098 -0.00330
0.00548 -0.00651
0.01338 -0.00827
0.02433 -0.00929
0.03811 -0.00989
0.05468 -0.01015
0.07395 -0.01007
0.09576 -0.00965
0.11999 -0.00891
0.14648 -0.00788
0.17504 -0.00656
0.20549 -0.00499
0.23760 -0.00323
0.27120 -0.00133
0.30609 0.00064
0.34204 0.00261
0.37887 0.00453
0.41638 0.00635
0.45435 0.00800
0.49265 0.00948
0.53099 0.01074
0.56937 0.01176
0.60778 0.01250
0.64594 0.01295
0.68359 0.01311
0.72043 0.01296
0.75616 0.01249
0.79048 0.01172
0.82309 0.01068
0.85370 0.00941
0.88202 0.00797
0.90775 0.00643
0.93064 0.00490
0.95044 0.00348
0.96698 0.00226
0.98037 0.00129
0.99070 0.00058
0.99754 0.00014
1.00000 -0.00002
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Polars for cr001sm (cr001sm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| cr001sm-il | 50,000 | 9 | 41.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cr001sm-il | 50,000 | 5 | 44.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cr001sm-il | 100,000 | 9 | 64.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cr001sm-il | 100,000 | 5 | 64.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cr001sm-il | 200,000 | 9 | 89.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cr001sm-il | 200,000 | 5 | 83.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cr001sm-il | 500,000 | 9 | 120.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cr001sm-il | 500,000 | 5 | 105.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cr001sm-il | 1,000,000 | 9 | 139.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cr001sm-il | 1,000,000 | 5 | 119.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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