NASA/LANGLEY RC-10(N)1 AIRFOIL (rc10n1-il)
NASA/LANGLEY RC-10(N)1 AIRFOIL - NASA/Langley RC-10(N)1 rotorcraft airfoil
| Details | Dat file | Parser | |
|
(rc10n1-il) NASA/LANGLEY RC-10(N)1 AIRFOIL NASA/Langley RC-10(N)1 rotorcraft airfoil Max thickness 10% at 37.6% chord. Max camber 1.5% at 25% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NASA/LANGLEY RC-10(N)1 AIRFOIL
42. 42.
0.0000000 0.0000000
0.0003866 0.0024921
0.0029418 0.0071358
0.0090205 0.0129684
0.0227769 0.0211120
0.0474860 0.0306243
0.0730883 0.0376612
0.0981790 0.0431053
0.1233345 0.0476397
0.1485640 0.0514847
0.1738364 0.0547297
0.1992019 0.0574154
0.2245202 0.0595907
0.2497209 0.0612954
0.3000885 0.0635346
0.3504139 0.0643737
0.3755741 0.0643080
0.4007059 0.0639023
0.4258298 0.0631666
0.4509657 0.0620610
0.4760634 0.0605952
0.5011227 0.0587892
0.5261840 0.0566631
0.5512268 0.0542470
0.5762510 0.0515606
0.6012866 0.0486143
0.6263436 0.0454283
0.6513818 0.0420121
0.6762308 0.0384150
0.7013906 0.0347093
0.7262403 0.0309821
0.7511899 0.0272955
0.7760184 0.0237582
0.8006660 0.0204498
0.8253926 0.0173219
0.8501882 0.0143845
0.8750428 0.0116272
0.8999864 0.0090505
0.9249590 0.0066640
0.9499204 0.0044974
0.9748908 0.0025409
1.0000000 0.0007950
0.0000000 0.0000000
0.0046360 -.0067353
0.0070624 -.0079423
0.0159667 -.0106348
0.0271678 -.0127149
0.0524352 -.0160000
0.0768090 -.0186097
0.1017018 -.0210367
0.1265236 -.0232440
0.1512840 -.0252317
0.1760034 -.0270296
0.2006319 -.0286380
0.2253096 -.0301161
0.2501065 -.0314535
0.2997282 -.0336884
0.3494062 -.0352628
0.3742391 -.0357901
0.3991207 -.0361071
0.4240010 -.0362142
0.4488701 -.0360812
0.4737781 -.0357181
0.4987149 -.0351246
0.5236606 -.0343214
0.5486248 -.0333180
0.5736086 -.0321544
0.5985816 -.0308609
0.6235239 -.0294676
0.6484961 -.0280242
0.6734582 -.0265907
0.6985109 -.0252267
0.7236739 -.0239323
0.7487371 -.0226983
0.7739201 -.0214336
0.7992724 -.0200081
0.8245534 -.0183430
0.8497628 -.0163982
0.8749009 -.0141938
0.8999681 -.0118398
0.9249951 -.0094160
0.9500216 -.0069522
0.9750472 -.0042784
1.0000000 -.0007950
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for NASA/LANGLEY RC-10(N)1 AIRFOIL (rc10n1-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rc10n1-il | 50,000 | 9 | 33.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc10n1-il | 50,000 | 5 | 33.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc10n1-il | 100,000 | 9 | 49 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc10n1-il | 100,000 | 5 | 46.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc10n1-il | 200,000 | 9 | 65.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc10n1-il | 200,000 | 5 | 59.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc10n1-il | 500,000 | 9 | 84.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc10n1-il | 500,000 | 5 | 70.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc10n1-il | 1,000,000 | 9 | 94.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc10n1-il | 1,000,000 | 5 | 78.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||