CH10 (smoothed) (ch10sm-il)
CH10 (smoothed) - Chuch Hollinger CH 10-48-13 high lift low Reynolds number airfoil
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(ch10sm-il) CH10 (smoothed) Chuch Hollinger CH 10-48-13 high lift low Reynolds number airfoil Max thickness 12.8% at 30.6% chord. Max camber 10.2% at 49.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
CH10 (smoothed)
1.00000 0.00005
0.99754 0.00169
0.99070 0.00579
0.98037 0.01111
0.96698 0.01721
0.95044 0.02452
0.93064 0.03317
0.90775 0.04292
0.88202 0.05367
0.85370 0.06522
0.82309 0.07725
0.79048 0.08942
0.75616 0.10143
0.72043 0.11298
0.68359 0.12384
0.64594 0.13374
0.60778 0.14243
0.56937 0.14970
0.53099 0.15538
0.49265 0.15942
0.45435 0.16176
0.41638 0.16240
0.37887 0.16133
0.34204 0.15862
0.30609 0.15434
0.27120 0.14859
0.23760 0.14148
0.20549 0.13310
0.17504 0.12355
0.14648 0.11291
0.11999 0.10132
0.09576 0.08896
0.07395 0.07611
0.05468 0.06312
0.03811 0.05032
0.02433 0.03793
0.01338 0.02615
0.00548 0.01531
0.00098 0.00586
0.00000 0.00014
0.00098 -0.00450
0.00548 -0.00914
0.01338 -0.01179
0.02433 -0.01269
0.03811 -0.01209
0.05468 -0.01028
0.07395 -0.00759
0.09576 -0.00435
0.11999 -0.00076
0.14648 0.00320
0.17504 0.00748
0.20549 0.01201
0.23760 0.01667
0.27120 0.02136
0.30609 0.02597
0.34204 0.03040
0.37887 0.03457
0.41638 0.03839
0.45435 0.04178
0.49265 0.04466
0.53099 0.04693
0.56937 0.04851
0.60778 0.04933
0.64594 0.04932
0.68359 0.04845
0.72043 0.04672
0.75616 0.04423
0.79048 0.04108
0.82309 0.03739
0.85370 0.03322
0.88202 0.02867
0.90775 0.02386
0.93064 0.01896
0.95044 0.01410
0.96698 0.00936
0.98037 0.00516
0.99070 0.00212
0.99754 0.00044
1.00000 -0.00006
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Polars for CH10 (smoothed) (ch10sm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ch10sm-il | 50,000 | 9 | 6.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ch10sm-il | 50,000 | 5 | 12.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ch10sm-il | 100,000 | 9 | 10.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ch10sm-il | 100,000 | 5 | 38.1 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ch10sm-il | 200,000 | 9 | 73.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ch10sm-il | 200,000 | 5 | 86.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ch10sm-il | 500,000 | 9 | 135.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ch10sm-il | 500,000 | 5 | 132.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ch10sm-il | 1,000,000 | 9 | 175.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ch10sm-il | 1,000,000 | 5 | 164 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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