NASA RC(5)-10 AIRFOIL (rc510-il)
NASA RC(5)-10 AIRFOIL - NASA/Langley RC(5)-10 rotorcraft airfoil
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(rc510-il) NASA RC(5)-10 AIRFOIL NASA/Langley RC(5)-10 rotorcraft airfoil Max thickness 10% at 40.1% chord. Max camber 2.2% at 25.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NASA RC(5)-10 AIRFOIL
41. 43.
0.0 0.0
0.0028699 0.0086493
0.0093564 0.0167131
0.0235851 0.0279240
0.0473197 0.0400544
0.0736415 0.0489540
0.0999394 0.0550586
0.1257977 0.0593046
0.1514405 0.0623730
0.1768159 0.0646707
0.2021529 0.0664675
0.2273750 0.0678983
0.2525969 0.0690471
0.3028524 0.0706359
0.3529137 0.0712934
0.3779400 0.0712125
0.4031252 0.0707934
0.4282423 0.0699861
0.4535508 0.0687381
0.4787810 0.0670466
0.5036672 0.0649649
0.5286227 0.0625196
0.5535420 0.0597777
0.5784435 0.0567727
0.6033537 0.0535177
0.6282811 0.0500196
0.6531860 0.0463035
0.6780995 0.0424016
0.7029201 0.0383913
0.7276346 0.0343608
0.7524412 0.0303697
0.7771370 0.0265333
0.8016555 0.0229112
0.8262545 0.0194796
0.8509200 0.0162354
0.8756557 0.0131708
0.9004740 0.0102825
0.9253236 0.0075900
0.9501698 0.0051105
0.9750257 0.0028500
1.0000000 0.0007915
0.0 0.0
0.0034372 -.0075914
0.0118775 -.0123999
0.0140497 -.0131715
0.0225541 -.0154813
0.0333092 -.0174415
0.0594707 -.0200039
0.0830337 -.0209595
0.1066037 -.0213593
0.1305989 -.0216152
0.1548014 -.0219837
0.1792631 -.0225632
0.2037586 -.0233070
0.2283655 -.0241226
0.2529693 -.0249422
0.3023628 -.0265038
0.3519449 -.0278438
0.3767368 -.0283788
0.4013711 -.0287866
0.4260693 -.0290409
0.4505748 -.0291107
0.4751559 -.0289921
0.5000805 -.0286501
0.5249348 -.0281196
0.5498234 -.0274273
0.5747297 -.0266091
0.5996258 -.0256969
0.6245024 -.0247285
0.6494011 -.0237263
0.6742911 -.0227151
0.6992709 -.0216984
0.7243580 -.0206727
0.7493522 -.0196272
0.7744606 -.0185186
0.7997481 -.0173013
0.8249566 -.0159384
0.8501026 -.0143781
0.8751813 -.0125892
0.9001801 -.0105498
0.9251504 -.0084511
0.9501257 -.0063184
0.9750936 -.0039747
1.0000000 -.0007915
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Polars for NASA RC(5)-10 AIRFOIL (rc510-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rc510-il | 50,000 | 9 | 31.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 50,000 | 5 | 32.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 100,000 | 9 | 46.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 100,000 | 5 | 43.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 200,000 | 9 | 60.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 200,000 | 5 | 54.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 500,000 | 9 | 76.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 500,000 | 5 | 75.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 1,000,000 | 9 | 94.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 1,000,000 | 5 | 92.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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