FX 63-158 AIRFOIL (fx63158-il)
FX 63-158 AIRFOIL - Wortmann FX 63-158 airfoil
| Details | Dat file | Parser | |
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(fx63158-il) FX 63-158 AIRFOIL Wortmann FX 63-158 airfoil Max thickness 15.8% at 33.9% chord. Max camber 3.8% at 37.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
FX 63-158 AIRFOIL
49. 49.
0.0000000 0.0000000
0.0010200 0.0082000
0.0042200 0.0166100
0.0096000 0.0240000
0.0170200 0.0315500
0.0265000 0.0390000
0.0380200 0.0470600
0.0515800 0.0538700
0.0669400 0.0628500
0.0842200 0.0695900
0.1033000 0.0778700
0.1240300 0.0840700
0.1464300 0.0913200
0.1703700 0.0966400
0.1955800 0.1025600
0.2222100 0.1066500
0.2499800 0.1109200
0.2789100 0.1134400
0.3086100 0.1158100
0.3393300 0.1164500
0.3705600 0.1166200
0.4024300 0.1151100
0.4346900 0.1130600
0.4673300 0.1094900
0.4999700 0.1055700
0.5327400 0.1007000
0.5652500 0.0957800
0.5975000 0.0902500
0.6293800 0.0848300
0.6607400 0.0790700
0.6913300 0.0735400
0.7211500 0.0677700
0.7499501 0.0622400
0.7777300 0.0566200
0.8043500 0.0512400
0.8297000 0.0458900
0.8535000 0.0407900
0.8753000 0.0358000
0.8964400 0.0310900
0.9157100 0.0265400
0.9329900 0.0222900
0.9484800 0.0182500
0.9619200 0.0144600
0.9734400 0.0108400
0.9829100 0.0075000
0.9903400 0.0046600
0.9957100 0.0024100
0.9989100 0.0008900
1.0000000 0.0000000
0.0000000 0.0000000
0.0010200 -.0020000
0.0042200 -.0043000
0.0096000 -.0071900
0.0170200 -.0095000
0.0265000 -.0128400
0.0380200 -.0149800
0.0515800 -.0190100
0.0669400 -.0220000
0.0842200 -.0248000
0.1033000 -.0268000
0.1240300 -.0300900
0.1464300 -.0318900
0.1703700 -.0347000
0.1955800 -.0361600
0.2222100 -.0383600
0.2499800 -.0392700
0.2789100 -.0407400
0.3086100 -.0410300
0.3393300 -.0416900
0.3705600 -.0412200
0.4024300 -.0409600
0.4346900 -.0396700
0.4673300 -.0384700
0.4999700 -.0363100
0.5327400 -.0340200
0.5652500 -.0304900
0.5975000 -.0262900
0.6293800 -.0208000
0.6607400 -.0150900
0.6913300 -.0092000
0.7211500 -.0039700
0.7499501 0.0009100
0.7777300 0.0048200
0.8043500 0.0081400
0.8297000 0.0105200
0.8535000 0.0122700
0.8753000 0.0131600
0.8964400 0.0135000
0.9157100 0.0131600
0.9329900 0.0123400
0.9484800 0.0109800
0.9619200 0.0091900
0.9734400 0.0070900
0.9829100 0.0048700
0.9903400 0.0028600
0.9957100 0.0012600
0.9989100 0.0002500
1.0000000 0.0000000
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Polars for FX 63-158 AIRFOIL (fx63158-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx63158-il | 50,000 | 9 | 6.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63158-il | 50,000 | 5 | 18.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63158-il | 100,000 | 9 | 47.5 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63158-il | 100,000 | 5 | 51.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63158-il | 200,000 | 9 | 72.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63158-il | 200,000 | 5 | 67.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63158-il | 500,000 | 9 | 76.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63158-il | 500,000 | 5 | 70.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63158-il | 1,000,000 | 9 | 85 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63158-il | 1,000,000 | 5 | 81.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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