RAE 2822 AIRFOIL (rae2822-il)
RAE 2822 AIRFOIL - RAE 2822 transonic airfoil
| Details | Dat file | Parser | |
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(rae2822-il) RAE 2822 AIRFOIL RAE 2822 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 |
RAE 2822 AIRFOIL
65. 65.
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 -.003160
0.002408 -.006308
0.005412 -.009443
0.009607 -.012559
0.014984 -.015649
0.021530 -.018707
0.029228 -.021722
0.038060 -.024685
0.048005 -.027586
0.059039 -.030416
0.071136 -.033170
0.084265 -.035843
0.098396 -.038431
0.113495 -.040929
0.129524 -.043326
0.146447 -.045610
0.164221 -.047773
0.182803 -.049805
0.202150 -.051694
0.222215 -.053427
0.242949 -.054994
0.264302 -.056376
0.286222 -.057547
0.308658 -.058459
0.331555 -.059046
0.354858 -.059236
0.378510 -.058974
0.402455 -.058224
0.426635 -.056979
0.450991 -.055257
0.475466 -.053099
0.500000 -.050563
0.524534 -.047719
0.549009 -.044642
0.573365 -.041397
0.597545 -.038043
0.621490 -.034631
0.645142 -.031207
0.668445 -.027814
0.691342 -.024495
0.713778 -.021289
0.735698 -.018232
0.757051 -.015357
0.777785 -.012690
0.797850 -.010244
0.817197 -.008027
0.835779 -.006048
0.853553 -.004314
0.870476 -.002829
0.886505 -.001592
0.901604 -.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 RAE 2822 AIRFOIL (rae2822-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rae2822-il | 50,000 | 9 | 25.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae2822-il | 50,000 | 5 | 27 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae2822-il | 100,000 | 9 | 37.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae2822-il | 100,000 | 5 | 37.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae2822-il | 200,000 | 9 | 53.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae2822-il | 200,000 | 5 | 49.1 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae2822-il | 500,000 | 9 | 70.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae2822-il | 500,000 | 5 | 57.4 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae2822-il | 1,000,000 | 9 | 79 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae2822-il | 1,000,000 | 5 | 69.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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