NACA 66 (p51htip-il)
NACA 66 - NACA 66
| Details | Dat file | Parser | |
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(p51htip-il) NACA 66 NACA 66 Max thickness 12% at 45% chord. Max camber 1.3% at 47.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA 66,2-(1.8)12 A=.6 P-51 TIP AIRFOIL
49.0 49.0
0.000000 0.000000
0.001859 0.006812
0.004112 0.009583
0.006512 0.011638
0.008943 0.013306
0.011393 0.014734
0.018795 0.018227
0.023749 0.020217
0.048596 0.028646
0.073528 0.035398
0.098509 0.041094
0.123521 0.046061
0.148558 0.050417
0.173613 0.054241
0.198683 0.057614
0.223765 0.060595
0.248857 0.063218
0.273958 0.065507
0.299067 0.067478
0.324183 0.069148
0.349305 0.070531
0.374432 0.071632
0.399566 0.072452
0.424704 0.072998
0.449848 0.073258
0.474998 0.073235
0.500154 0.072920
0.525318 0.072297
0.550494 0.071343
0.575689 0.070027
0.600951 0.068244
0.626185 0.065839
0.651298 0.062766
0.676347 0.059107
0.701348 0.055022
0.726309 0.050640
0.751239 0.046002
0.776140 0.041128
0.801018 0.036064
0.825880 0.030891
0.850731 0.025693
0.875577 0.020538
0.900424 0.015492
0.925280 0.010663
0.950152 0.006221
0.975052 0.002442
0.985023 0.001227
0.990012 0.000715
1.000000 0.000000
0.000000 0.000000
0.003141 -0.006166
0.005888 -0.008416
0.008488 -0.009997
0.011057 -0.011222
0.013607 -0.012230
0.021205 -0.014561
0.026251 -0.015837
0.051404 -0.021157
0.076472 -0.025298
0.101491 -0.028721
0.126479 -0.031672
0.151442 -0.034228
0.176387 -0.036436
0.201317 -0.038359
0.226235 -0.040042
0.251143 -0.041506
0.276042 -0.042768
0.300933 -0.043840
0.325817 -0.044733
0.350695 -0.045457
0.375568 -0.046017
0.400434 -0.046414
0.425296 -0.046652
0.450152 -0.046726
0.475002 -0.046638
0.499846 -0.046386
0.524682 -0.045961
0.549506 -0.045352
0.574311 -0.044546
0.599049 -0.043476
0.623815 -0.042061
0.648702 -0.040170
0.673653 -0.037840
0.698652 -0.035198
0.723691 -0.032354
0.748761 -0.029328
0.773860 -0.026125
0.798982 -0.022776
0.824120 -0.019344
0.849269 -0.015901
0.874423 -0.012499
0.899576 -0.009187
0.924720 -0.006055
0.949848 -0.003252
0.974948 -0.001024
0.984977 -0.000398
0.989988 -0.000170
1.000000 0.000000
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Similar airfoils
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Polars for NACA 66 (p51htip-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| p51htip-il | 50,000 | 9 | 22.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51htip-il | 50,000 | 5 | 22.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51htip-il | 100,000 | 9 | 35.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51htip-il | 100,000 | 5 | 38.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51htip-il | 200,000 | 9 | 52.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51htip-il | 200,000 | 5 | 48 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51htip-il | 500,000 | 9 | 72.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51htip-il | 500,000 | 5 | 67 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51htip-il | 1,000,000 | 9 | 90.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51htip-il | 1,000,000 | 5 | 75.1 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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