NACA/LANGLEY SYMMETRICAL (n0011sc-il)
NACA/LANGLEY SYMMETRICAL - NASA/Langley 11% symmetrical supercritical airfoil
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(n0011sc-il) NACA/LANGLEY SYMMETRICAL NASA/Langley 11% symmetrical supercritical airfoil Max thickness 11% at 40% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA/LANGLEY SYMMETRICAL, SUPERCRITICAL AIRFOIL
37. 37.
0.0000000 0.0000000
0.0020000 0.0092250
0.0065243 0.0157510
0.0125000 0.0203230
0.0250000 0.0262080
0.0375000 0.0302420
0.0500000 0.0333730
0.0750000 0.0381170
0.1000000 0.0416430
0.1250000 0.0444000
0.1500000 0.0466150
0.1750000 0.0484210
0.2000000 0.0499050
0.2500000 0.0521250
0.3000000 0.0535880
0.3500000 0.0544670
0.4000000 0.0547830
0.4500000 0.0545710
0.5000000 0.0537580
0.5500000 0.0523760
0.6000000 0.0504100
0.6250000 0.0491980
0.6500000 0.0478240
0.6750000 0.0462810
0.7000000 0.0445560
0.7250000 0.0426350
0.7500000 0.0404990
0.7750000 0.0381270
0.8000000 0.0354920
0.8250000 0.0325640
0.8500000 0.0293060
0.8750000 0.0256760
0.9000000 0.0216250
0.9250000 0.0170990
0.9500000 0.0120340
0.9750000 0.0063610
1.0000000 0.0000000
0.0000000 0.0000000
0.0020000 -.0092250
0.0065243 -.0157510
0.0125000 -.0203230
0.0250000 -.0262080
0.0375000 -.0302420
0.0500000 -.0333730
0.0750000 -.0381170
0.1000000 -.0416430
0.1250000 -.0444000
0.1500000 -.0466150
0.1750000 -.0484210
0.2000000 -.0499050
0.2500000 -.0521250
0.3000000 -.0535880
0.3500000 -.0544670
0.4000000 -.0547830
0.4500000 -.0545710
0.5000000 -.0537580
0.5500000 -.0523760
0.6000000 -.0504100
0.6250000 -.0491980
0.6500000 -.0478240
0.6750000 -.0462810
0.7000000 -.0445560
0.7250000 -.0426350
0.7500000 -.0404990
0.7750000 -.0381270
0.8000000 -.0354920
0.8250000 -.0325640
0.8500000 -.0293060
0.8750000 -.0256760
0.9000000 -.0216250
0.9250000 -.0170990
0.9500000 -.0120340
0.9750000 -.0063610
1.0000000 0.0000000
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Polars for NACA/LANGLEY SYMMETRICAL (n0011sc-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n0011sc-il | 50,000 | 9 | 22.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n0011sc-il | 50,000 | 5 | 22.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n0011sc-il | 100,000 | 9 | 30.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n0011sc-il | 100,000 | 5 | 30.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n0011sc-il | 200,000 | 9 | 41.5 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n0011sc-il | 200,000 | 5 | 39.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n0011sc-il | 500,000 | 9 | 49.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n0011sc-il | 500,000 | 5 | 50.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n0011sc-il | 1,000,000 | 9 | 59 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n0011sc-il | 1,000,000 | 5 | 62.6 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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