FX 61-168 AIRFOIL (fx61168-il)
FX 61-168 AIRFOIL - Wortmann FX 61-168 airfoil
| Details | Dat file | Parser | |
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(fx61168-il) FX 61-168 AIRFOIL Wortmann FX 61-168 airfoil Max thickness 16.8% at 37.1% chord. Max camber 3% at 37.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
FX 61-168 AIRFOIL
49. 49.
0.0000000 0.0000000
0.0010200 0.0066800
0.0042200 0.0137700
0.0096000 0.0210700
0.0170200 0.0286100
0.0265000 0.0364300
0.0380200 0.0445300
0.0515800 0.0525600
0.0669400 0.0604900
0.0842200 0.0680800
0.1033000 0.0753800
0.1240300 0.0821900
0.1464300 0.0886100
0.1703700 0.0944200
0.1955800 0.0996600
0.2222100 0.1041300
0.2499800 0.1078600
0.2789100 0.1106900
0.3086100 0.1126900
0.3393300 0.1137300
0.3705600 0.1139300
0.4024300 0.1131600
0.4346900 0.1114600
0.4673300 0.1086400
0.4999700 0.1048200
0.5327400 0.1000700
0.5652500 0.0947400
0.5975000 0.0890400
0.6293800 0.0832500
0.6607400 0.0773800
0.6913300 0.0715400
0.7211500 0.0657100
0.7499501 0.0599900
0.7777300 0.0543700
0.8043500 0.0489600
0.8297000 0.0437500
0.8535000 0.0387800
0.8759000 0.0340300
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 -.0021900
0.0042200 -.0055200
0.0096000 -.0090100
0.0170200 -.0125800
0.0265000 -.0163000
0.0380200 -.0199600
0.0515800 -.0236600
0.0669400 -.0272800
0.0842200 -.0308700
0.1033000 -.0343300
0.1240300 -.0377100
0.1464300 -.0409000
0.1703700 -.0438900
0.1955800 -.0467300
0.2222100 -.0491900
0.2499800 -.0512000
0.2789100 -.0526700
0.3086100 -.0536300
0.3393300 -.0540700
0.3705600 -.0541300
0.4024300 -.0535800
0.4346900 -.0523800
0.4673300 -.0504500
0.4999700 -.0478400
0.5327400 -.0445700
0.5652500 -.0405800
0.5975000 -.0357600
0.6293800 -.0301900
0.6607400 -.0241800
0.6913300 -.0181700
0.7211500 -.0126200
0.7499501 -.0077000
0.7777300 -.0034500
0.8043500 0.0001400
0.8297000 0.0030800
0.8535000 0.0053700
0.8759000 0.0070100
0.8964400 0.0080500
0.9157100 0.0085100
0.9329900 0.0084400
0.9484800 0.0078800
0.9619200 0.0069100
0.9734400 0.0056100
0.9829100 0.0041200
0.9903400 0.0028100
0.9957100 0.0015000
0.9989100 0.0004000
1.0000000 0.0000000
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Polars for FX 61-168 AIRFOIL (fx61168-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx61168-il | 50,000 | 9 | 5.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61168-il | 50,000 | 5 | 15.4 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61168-il | 100,000 | 9 | 44.7 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61168-il | 100,000 | 5 | 48.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61168-il | 200,000 | 9 | 71 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61168-il | 200,000 | 5 | 73 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61168-il | 500,000 | 9 | 104.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61168-il | 500,000 | 5 | 101.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61168-il | 1,000,000 | 9 | 129.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61168-il | 1,000,000 | 5 | 120.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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