CHEN AIRFOIL (chen-il)
CHEN AIRFOIL - University of Illinois at Urbana-Champaign / Chen high lift airfoil
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(chen-il) CHEN AIRFOIL University of Illinois at Urbana-Champaign / Chen high lift airfoil Max thickness 12.5% at 27.7% chord. Max camber 7.8% at 25.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
CHEN AIRFOIL
51. 48.
0.0000000 0.0000000
0.0003558 0.0017755
0.0018436 0.0084703
0.0047082 0.0160470
0.0090325 0.0242980
0.0147986 0.0330236
0.0220880 0.0420161
0.0304777 0.0510117
0.0407061 0.0604470
0.0522330 0.0698676
0.0651491 0.0791655
0.0793468 0.0882499
0.0949072 0.0969123
0.1115329 0.1051795
0.1293059 0.1128435
0.1482170 0.1198041
0.1679599 0.1259887
0.1885260 0.1312975
0.2098976 0.1355311
0.2319581 0.1384987
0.2543924 0.1400281
0.2771567 0.1396213
0.2997316 0.1359180
0.3245689 0.1295050
0.3532844 0.1228496
0.3839673 0.1158192
0.4161386 0.1086572
0.4493841 0.1011996
0.4836304 0.0937538
0.5185713 0.0862464
0.5540261 0.0788946
0.5895069 0.0718414
0.6249059 0.0649964
0.6599432 0.0585850
0.6943033 0.0524342
0.7278053 0.0467607
0.7601339 0.0413920
0.7911083 0.0365444
0.8205041 0.0319369
0.8482387 0.0277774
0.8739075 0.0240015
0.8976089 0.0206002
0.9190280 0.0174009
0.9380744 0.0145117
0.9546400 0.0118420
0.9688153 0.0092833
0.9802941 0.0067623
0.9890499 0.0039802
0.9954385 0.0027124
0.9987892 0.0010106
1.0000000 0.0000000
0.0000000 0.0000000
0.0001465 -.0040284
0.0011596 -.0084347
0.0031979 -.0114257
0.0061967 -.0136988
0.0106477 -.0153975
0.0175501 -.0165099
0.0265157 -.0169012
0.0375885 -.0160736
0.0517692 -.0140150
0.0690841 -.0104265
0.0864429 -.0063401
0.1068134 -.0021185
0.1271930 0.0022028
0.1496093 0.0069462
0.1759774 0.0111393
0.2062535 0.0142842
0.2263533 0.0154178
0.2663509 0.0153939
0.2962248 0.0139564
0.3260373 0.0118217
0.3587833 0.0089256
0.3885173 0.0058943
0.4177550 0.0029070
0.4567609 -.0004423
0.4935460 -.0028925
0.5295632 -.0049737
0.5648774 -.0070930
0.5994238 -.0088433
0.6332201 -.0100253
0.6662313 -.0110375
0.6983493 -.0119707
0.7297727 -.0128425
0.7600055 -.0136089
0.7888490 -.0142526
0.8164113 -.0146824
0.8425377 -.0143830
0.8669041 -.0136268
0.8899892 -.0126568
0.9114051 -.0113384
0.9306377 -.0098270
0.9479849 -.0081488
0.9630589 -.0061692
0.9756256 -.0042691
0.9856419 -.0029464
0.9930255 -.0019932
0.9980277 -.0008293
1.0000000 0.0000000
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Polars for CHEN AIRFOIL (chen-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| chen-il | 50,000 | 9 | 4.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| chen-il | 50,000 | 5 | 4.8 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| chen-il | 100,000 | 9 | 4.9 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| chen-il | 100,000 | 5 | 8.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| chen-il | 200,000 | 9 | 5.6 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| chen-il | 200,000 | 5 | 19.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| chen-il | 500,000 | 9 | 13.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| chen-il | 500,000 | 5 | 56.5 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| chen-il | 1,000,000 | 9 | 125.4 at α=14.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| chen-il | 1,000,000 | 5 | 123 at α=13° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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