S5010 (s5010-il)
S5010 - Selig S5010 low Reynolds number airfoil
| Details | Dat file | Parser | |
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(s5010-il) S5010 Selig S5010 low Reynolds number airfoil Max thickness 9.8% at 27.6% chord. Max camber 1.8% at 32% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S5010
1.0000000 0.0000000
0.9967600 0.0000100
0.9870700 0.0000700
0.9710100 0.0003600
0.9487000 0.0010800
0.9204100 0.0025600
0.8866700 0.0051600
0.8482800 0.0090300
0.8060800 0.0140600
0.7607600 0.0200800
0.7130700 0.0268800
0.6637700 0.0342000
0.6135500 0.0416300
0.5629600 0.0487700
0.5124700 0.0552900
0.4625100 0.0609300
0.4134600 0.0654600
0.3657600 0.0687300
0.3196900 0.0706300
0.2756000 0.0711300
0.2338300 0.0702300
0.1947300 0.0679900
0.1586000 0.0644500
0.1257300 0.0596800
0.0963700 0.0537700
0.0707100 0.0468800
0.0488900 0.0391500
0.0310200 0.0308100
0.0171800 0.0221400
0.0073900 0.0134800
0.0016700 0.0053300
0.0001500 -0.0014000
0.0042400 -0.0065000
0.0145600 -0.0108400
0.0302800 -0.0147100
0.0512300 -0.0180400
0.0771800 -0.0208200
0.1078500 -0.0230600
0.1429100 -0.0248100
0.1819400 -0.0260900
0.2244800 -0.0268800
0.2700800 -0.0271500
0.3182900 -0.0269100
0.3686400 -0.0262300
0.4205500 -0.0251700
0.4734500 -0.0238100
0.5267500 -0.0221900
0.5798300 -0.0203900
0.6320900 -0.0184600
0.6829200 -0.0164500
0.7317300 -0.0144300
0.7779200 -0.0124300
0.8209500 -0.0104900
0.8603000 -0.0086500
0.8954700 -0.0069100
0.9260300 -0.0052700
0.9516300 -0.0036700
0.9721100 -0.0021200
0.9873000 -0.0008800
0.9967800 -0.0001900
1.0000000 0.0000000
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Polars for S5010 (s5010-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s5010-il | 50,000 | 9 | 24.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5010-il | 50,000 | 5 | 32.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5010-il | 100,000 | 9 | 45 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5010-il | 100,000 | 5 | 47.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5010-il | 200,000 | 9 | 63.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5010-il | 200,000 | 5 | 62.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5010-il | 500,000 | 9 | 86.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5010-il | 500,000 | 5 | 80.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5010-il | 1,000,000 | 9 | 102.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5010-il | 1,000,000 | 5 | 94.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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