ONERA NACA CAMBRE AIRFOIL (ncambre-il)
ONERA NACA CAMBRE AIRFOIL - ONERA/Aerospatiale NACA-CAMBRE rotorcraft airfoil
| Details | Dat file | Parser | |
|
(ncambre-il) ONERA NACA CAMBRE AIRFOIL ONERA/Aerospatiale NACA-CAMBRE rotorcraft airfoil Max thickness 11.5% at 31.2% chord. Max camber 1.4% at 15.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
ONERA NACA CAMBRE AIRFOIL
40. 40.
0.0000000 0.0000000
0.0057369 0.0140050
0.0107226 0.0190715
0.0199450 0.0263167
0.0298495 0.0325002
0.0408460 0.0382151
0.0507159 0.0423489
0.0604739 0.0457845
0.0715299 0.0490981
0.0862933 0.0528492
0.1009467 0.0560020
0.1205035 0.0593718
0.1410517 0.0622250
0.1590854 0.0642205
0.1781121 0.0657991
0.1961324 0.0669947
0.2271574 0.0684705
0.2571690 0.0691635
0.2881728 0.0693895
0.3121702 0.0692340
0.3311630 0.0688130
0.3671460 0.0678047
0.4161084 0.0655769
0.4510713 0.0633857
0.5010130 0.0599414
0.5379637 0.0570164
0.5739095 0.0538085
0.6108516 0.0503837
0.6467889 0.0466758
0.6837226 0.0427511
0.7326309 0.0373238
0.7685580 0.0330160
0.8174545 0.0268888
0.8543746 0.0221642
0.8783188 0.0188591
0.9152339 0.0138345
0.9391746 0.0103294
0.9631137 0.0067243
0.9750832 0.0049218
1.0000000 0.0011998
0.0000000 0.0000000
0.0053179 -.0107914
0.0101642 -.0139738
0.0192092 -.0172271
0.0289692 -.0195924
0.0398341 -.0216763
0.0496042 -.0234416
0.0592794 -.0249054
0.0702476 -.0267910
0.0849181 -.0285392
0.0994869 -.0303857
0.1189492 -.0326149
0.1394129 -.0347610
0.1573842 -.0364650
0.1763551 -.0381858
0.1943262 -.0398897
0.2252854 -.0423133
0.2552564 -.0440201
0.2862349 -.0452937
0.3102239 -.0459492
0.3292201 -.0461703
0.3652166 -.0463787
0.4142263 -.0458068
0.4492432 -.0447985
0.4992728 -.0430438
0.5363012 -.0413693
0.5723349 -.0393780
0.6093715 -.0372036
0.6454136 -.0347124
0.6824589 -.0320381
0.7315226 -.0282667
0.7675747 -.0251756
0.8166503 -.0207043
0.8537089 -.0172301
0.8777511 -.0147361
0.9148149 -.0109619
0.9388604 -.0082679
0.9629076 -.0054739
0.9749312 -.0040769
1.0000000 -.0011998
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for ONERA NACA CAMBRE AIRFOIL (ncambre-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ncambre-il | 50,000 | 9 | 26.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ncambre-il | 50,000 | 5 | 29.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ncambre-il | 100,000 | 9 | 39.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ncambre-il | 100,000 | 5 | 41.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ncambre-il | 200,000 | 9 | 52.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ncambre-il | 200,000 | 5 | 54.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ncambre-il | 500,000 | 9 | 73.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ncambre-il | 500,000 | 5 | 73 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ncambre-il | 1,000,000 | 9 | 90.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ncambre-il | 1,000,000 | 5 | 88 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||