RAE6-9CK AIRFOIL (rae69ck-il)
RAE6-9CK AIRFOIL - RAE6-9CK transonic airfoil
| Details | Dat file | Parser | |
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(rae69ck-il) RAE6-9CK AIRFOIL RAE6-9CK transonic airfoil Max thickness 12.1% at 37.9% chord. Max camber 1.3% at 75.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
RAE6-9CK AIRFOIL
65.0 65.0
0.000000 0.000000
0.000602 0.003165
0.002408 0.006306
0.005412 0.009416
0.009607 0.012480
0.014984 0.015489
0.021530 0.018441
0.029228 0.021348
0.038060 0.024219
0.048005 0.027062
0.059039 0.029874
0.071136 0.032644
0.084265 0.035360
0.098396 0.038011
0.113495 0.040585
0.129524 0.043071
0.146447 0.045457
0.164221 0.047729
0.182803 0.049874
0.202150 0.051885
0.222215 0.053753
0.242949 0.055470
0.264302 0.057026
0.286222 0.058414
0.308658 0.059629
0.331555 0.060660
0.354858 0.061497
0.378510 0.062133
0.402455 0.062562
0.426635 0.062779
0.450991 0.062774
0.475466 0.062530
0.500000 0.062029
0.524534 0.061254
0.549009 0.060194
0.573365 0.058845
0.597545 0.057218
0.621490 0.055344
0.645142 0.053258
0.668445 0.050993
0.691342 0.048575
0.713778 0.046029
0.735698 0.043377
0.757051 0.040641
0.777785 0.037847
0.797850 0.035017
0.817197 0.032176
0.835779 0.029347
0.853553 0.026554
0.870476 0.023817
0.886505 0.021153
0.901604 0.018580
0.915735 0.016113
0.928864 0.013769
0.940961 0.011562
0.951995 0.009508
0.961940 0.007622
0.970772 0.005915
0.978470 0.004401
0.985016 0.003092
0.990393 0.002001
0.994588 0.001137
0.997592 0.000510
0.999398 0.000128
1.000000 0.000000
0.000000 0.000000
0.000602 -0.003160
0.002408 -0.006308
0.005412 -0.009443
0.009607 -0.012559
0.014984 -0.015649
0.021530 -0.018707
0.029228 -0.021722
0.038060 -0.024685
0.048005 -0.027586
0.059039 -0.030416
0.071136 -0.033170
0.084265 -0.035843
0.098396 -0.038431
0.113495 -0.040929
0.129524 -0.043326
0.146447 -0.045610
0.164221 -0.047773
0.182803 -0.049805
0.202150 -0.051694
0.222215 -0.053427
0.242949 -0.054994
0.264302 -0.056376
0.286222 -0.057547
0.308658 -0.058459
0.331555 -0.059046
0.354858 -0.059236
0.378510 -0.058974
0.402455 -0.058224
0.426635 -0.056979
0.450991 -0.055257
0.475466 -0.053099
0.500000 -0.050563
0.524534 -0.047719
0.549009 -0.044642
0.573365 -0.041397
0.597545 -0.038043
0.621490 -0.034631
0.645142 -0.031207
0.668445 -0.027814
0.691342 -0.024495
0.713778 -0.021289
0.735698 -0.018232
0.757051 -0.015357
0.777785 -0.012690
0.797850 -0.010244
0.817197 -0.008027
0.835779 -0.006048
0.853553 -0.004314
0.870476 -0.002829
0.886505 -0.001592
0.901604 -0.000600
0.915735 0.000157
0.928864 0.000694
0.940961 0.001033
0.951995 0.001197
0.961940 0.001212
0.970772 0.001112
0.978470 0.000935
0.985016 0.000719
0.990393 0.000497
0.994588 0.000296
0.997592 0.000137
0.999398 0.000035
1.000000 0.000000
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Polars for RAE6-9CK AIRFOIL (rae69ck-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rae69ck-il | 50,000 | 9 | 25.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae69ck-il | 50,000 | 5 | 27 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae69ck-il | 100,000 | 9 | 37.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae69ck-il | 100,000 | 5 | 37.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae69ck-il | 200,000 | 9 | 53.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae69ck-il | 200,000 | 5 | 49.1 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae69ck-il | 500,000 | 9 | 70.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae69ck-il | 500,000 | 5 | 57.4 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae69ck-il | 1,000,000 | 9 | 79 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae69ck-il | 1,000,000 | 5 | 69.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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