FX 61-147 AIRFOIL (fx61147-il)
FX 61-147 AIRFOIL - Wortmann FX 61-147 airfoil
| Details | Dat file | Parser | |
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(fx61147-il) FX 61-147 AIRFOIL Wortmann FX 61-147 airfoil Max thickness 14.8% at 33.9% chord. Max camber 3.2% at 33.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
FX 61-147 AIRFOIL
49. 49.
0.0000000 0.0000000
0.0010200 0.0068800
0.0042200 0.0132200
0.0096000 0.0199600
0.0170200 0.0269800
0.0265000 0.0344000
0.0380200 0.0420400
0.0515800 0.0496500
0.0669400 0.0572100
0.0842200 0.0645500
0.1033000 0.0716500
0.1240300 0.0783100
0.1464300 0.0845300
0.1700000 0.0900600
0.1955800 0.0948900
0.2222100 0.0988300
0.2499800 0.1019400
0.2789100 0.1041000
0.3086100 0.1053700
0.3393300 0.1056700
0.3705600 0.1051100
0.4024300 0.1036600
0.4346900 0.1015100
0.4673300 0.0987000
0.4999700 0.0953900
0.5327400 0.0916400
0.5652500 0.0875400
0.5975000 0.0831500
0.6293800 0.0785500
0.6607400 0.0737800
0.6913300 0.0688800
0.7211500 0.0638800
0.7499501 0.0588200
0.7777300 0.0537500
0.8043500 0.0487100
0.8297000 0.0437000
0.8535000 0.0388000
0.8759000 0.0340500
0.8964400 0.0295300
0.9157100 0.0252500
0.9329900 0.0212100
0.9484800 0.0174100
0.9619200 0.0138200
0.9734400 0.0104700
0.9829100 0.0074100
0.9903400 0.0048400
0.9957100 0.0026600
0.9989100 0.0009900
1.0000000 0.0000000
0.0000000 0.0000000
0.0010200 -.0016600
0.0042200 -.0047500
0.0096000 -.0078900
0.0170200 -.0109900
0.0265000 -.0140900
0.0380200 -.0170800
0.0515800 -.0200100
0.0669400 -.0228800
0.0842200 -.0257000
0.1033000 -.0283900
0.1240300 -.0309300
0.1464300 -.0332700
0.1700000 -.0354200
0.1955800 -.0373000
0.2222100 -.0389200
0.2499800 -.0402300
0.2789100 -.0412000
0.3086100 -.0418000
0.3393300 -.0419900
0.3705600 -.0417400
0.4024300 -.0410300
0.4346900 -.0398000
0.4673300 -.0380500
0.4999700 -.0357400
0.5327400 -.0328800
0.5652500 -.0295000
0.5975000 -.0255200
0.6293800 -.0209600
0.6607400 -.0159200
0.6913300 -.0107000
0.7211500 -.0056500
0.7499501 -.0011500
0.7777300 0.0026500
0.8043500 0.0056800
0.8297000 0.0079300
0.8535000 0.0093900
0.8759000 0.0101200
0.8964400 0.0102500
0.9157100 0.0099000
0.9329900 0.0091700
0.9484800 0.0081900
0.9619200 0.0069800
0.9734400 0.0055900
0.9829100 0.0040900
0.9903400 0.0027600
0.9957100 0.0014800
0.9989100 0.0004000
1.0000000 0.0000000
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Polars for FX 61-147 AIRFOIL (fx61147-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx61147-il | 50,000 | 9 | 8.4 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61147-il | 50,000 | 5 | 28.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61147-il | 100,000 | 9 | 50 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61147-il | 100,000 | 5 | 52.3 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61147-il | 200,000 | 9 | 70.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61147-il | 200,000 | 5 | 71.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61147-il | 500,000 | 9 | 99.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61147-il | 500,000 | 5 | 98.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61147-il | 1,000,000 | 9 | 123.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61147-il | 1,000,000 | 5 | 119.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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