CLARK Y AIRFOIL (clarky-il)
CLARK Y AIRFOIL - CLARK Y airfoil
| Details | Dat file | Parser | |
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(clarky-il) CLARK Y AIRFOIL CLARK Y airfoil Max thickness 11.7% at 28% chord. Max camber 3.4% at 42% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
CLARK Y AIRFOIL
61.0 61.0
0.0000000 0.0000000
0.0005000 0.0023390
0.0010000 0.0037271
0.0020000 0.0058025
0.0040000 0.0089238
0.0080000 0.0137350
0.0120000 0.0178581
0.0200000 0.0253735
0.0300000 0.0330215
0.0400000 0.0391283
0.0500000 0.0442753
0.0600000 0.0487571
0.0800000 0.0564308
0.1000000 0.0629981
0.1200000 0.0686204
0.1400000 0.0734360
0.1600000 0.0775707
0.1800000 0.0810687
0.2000000 0.0839202
0.2200000 0.0861433
0.2400000 0.0878308
0.2600000 0.0890840
0.2800000 0.0900016
0.3000000 0.0906804
0.3200000 0.0911857
0.3400000 0.0915079
0.3600000 0.0916266
0.3800000 0.0915212
0.4000000 0.0911712
0.4200000 0.0905657
0.4400000 0.0897175
0.4600000 0.0886427
0.4800000 0.0873572
0.5000000 0.0858772
0.5200000 0.0842145
0.5400000 0.0823712
0.5600000 0.0803480
0.5800000 0.0781451
0.6000000 0.0757633
0.6200000 0.0732055
0.6400000 0.0704822
0.6600000 0.0676046
0.6800000 0.0645843
0.7000000 0.0614329
0.7200000 0.0581599
0.7400000 0.0547675
0.7600000 0.0512565
0.7800000 0.0476281
0.8000000 0.0438836
0.8200000 0.0400245
0.8400000 0.0360536
0.8600000 0.0319740
0.8800000 0.0277891
0.9000000 0.0235025
0.9200000 0.0191156
0.9400000 0.0146239
0.9600000 0.0100232
0.9700000 0.0076868
0.9800000 0.0053335
0.9900000 0.0029690
1.0000000 0.0005993
0.0000000 0.0000000
0.0005000 -.0046700
0.0010000 -.0059418
0.0020000 -.0078113
0.0040000 -.0105126
0.0080000 -.0142862
0.0120000 -.0169733
0.0200000 -.0202723
0.0300000 -.0226056
0.0400000 -.0245211
0.0500000 -.0260452
0.0600000 -.0271277
0.0800000 -.0284595
0.1000000 -.0293786
0.1200000 -.0299633
0.1400000 -.0302404
0.1600000 -.0302546
0.1800000 -.0300490
0.2000000 -.0296656
0.2200000 -.0291445
0.2400000 -.0285181
0.2600000 -.0278164
0.2800000 -.0270696
0.3000000 -.0263079
0.3200000 -.0255565
0.3400000 -.0248176
0.3600000 -.0240870
0.3800000 -.0233606
0.4000000 -.0226341
0.4200000 -.0219042
0.4400000 -.0211708
0.4600000 -.0204353
0.4800000 -.0196986
0.5000000 -.0189619
0.5200000 -.0182262
0.5400000 -.0174914
0.5600000 -.0167572
0.5800000 -.0160232
0.6000000 -.0152893
0.6200000 -.0145551
0.6400000 -.0138207
0.6600000 -.0130862
0.6800000 -.0123515
0.7000000 -.0116169
0.7200000 -.0108823
0.7400000 -.0101478
0.7600000 -.0094133
0.7800000 -.0086788
0.8000000 -.0079443
0.8200000 -.0072098
0.8400000 -.0064753
0.8600000 -.0057408
0.8800000 -.0050063
0.9000000 -.0042718
0.9200000 -.0035373
0.9400000 -.0028028
0.9600000 -.0020683
0.9700000 -.0017011
0.9800000 -.0013339
0.9900000 -.0009666
1.0000000 -.0005993
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Polars for CLARK Y AIRFOIL (clarky-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| clarky-il | 50,000 | 9 | 29.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarky-il | 50,000 | 5 | 36.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarky-il | 100,000 | 9 | 53 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarky-il | 100,000 | 5 | 54.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarky-il | 200,000 | 9 | 73.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarky-il | 200,000 | 5 | 69.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarky-il | 500,000 | 9 | 98.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarky-il | 500,000 | 5 | 90.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarky-il | 1,000,000 | 9 | 114.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarky-il | 1,000,000 | 5 | 108.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||