FX 61-184 AIRFOIL (fx61184-il)
FX 61-184 AIRFOIL - Wortmann FX 61-184 airfoil
| Details | Dat file | Parser | |
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(fx61184-il) FX 61-184 AIRFOIL Wortmann FX 61-184 airfoil Max thickness 18.4% at 37.1% chord. Max camber 3.1% at 62.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
FX 61-184 AIRFOIL
49. 49.
0.0000000 0.0000000
0.0010200 0.0081200
0.0042200 0.0152000
0.0096000 0.0225100
0.0170200 0.0300600
0.0265000 0.0379000
0.0380200 0.0459800
0.0515800 0.0540700
0.0669400 0.0620500
0.0842200 0.0698000
0.1033000 0.0772400
0.1240300 0.0842700
0.1464300 0.0908200
0.1703700 0.0968100
0.1955800 0.1022800
0.2222100 0.1071000
0.2499800 0.1112700
0.2789100 0.1146600
0.3086100 0.1172400
0.3393300 0.1189300
0.3705600 0.1197300
0.4024300 0.1195800
0.4346900 0.1185000
0.4673300 0.1164600
0.4999700 0.1135500
0.5327400 0.1097400
0.5652500 0.1051100
0.5975000 0.0995800
0.6293800 0.0932300
0.6607400 0.0861900
0.6913300 0.0787700
0.7211500 0.0712500
0.7499501 0.0639500
0.7777300 0.0569500
0.8043500 0.0503500
0.8297000 0.0441700
0.8535000 0.0384200
0.8759000 0.0330900
0.8964400 0.0281900
0.9157100 0.0236900
0.9329900 0.0195700
0.9484800 0.0158000
0.9619200 0.0123400
0.9734400 0.0092000
0.9829100 0.0064000
0.9903400 0.0040800
0.9957100 0.0021800
0.9989100 0.0007900
1.0000000 0.0000000
0.0000000 0.0000000
0.0010200 -.0024300
0.0042200 -.0067100
0.0096000 -.0110300
0.0170200 -.0153800
0.0265000 -.0197500
0.0380200 -.0241400
0.0515800 -.0285100
0.0669400 -.0328500
0.0842200 -.0371300
0.1033000 -.0412900
0.1240300 -.0452900
0.1464300 -.0490600
0.1703700 -.0525100
0.1955800 -.0556000
0.2222100 -.0583100
0.2499800 -.0605500
0.2789100 -.0623000
0.3086100 -.0634900
0.3393300 -.0640700
0.3705600 -.0640000
0.4024300 -.0632000
0.4346900 -.0615600
0.4673300 -.0589500
0.4999700 -.0552400
0.5327400 -.0504200
0.5652500 -.0446200
0.5975000 -.0381700
0.6293800 -.0314800
0.6607400 -.0249500
0.6913300 -.0188800
0.7211500 -.0134000
0.7499501 -.0085300
0.7777300 -.0043100
0.8043500 -.0007500
0.8297000 0.0021500
0.8535000 0.0044000
0.8759000 0.0060100
0.8964400 0.0070200
0.9157100 0.0074700
0.9329900 0.0074200
0.9484800 0.0069600
0.9619200 0.0061000
0.9734400 0.0049400
0.9829100 0.0036100
0.9903400 0.0024400
0.9957100 0.0012900
0.9989100 0.0003100
1.0000000 0.0000000
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Polars for FX 61-184 AIRFOIL (fx61184-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx61184-il | 50,000 | 9 | 5.7 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61184-il | 50,000 | 5 | 15.2 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61184-il | 100,000 | 9 | 39.8 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61184-il | 100,000 | 5 | 43.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61184-il | 200,000 | 9 | 69.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61184-il | 200,000 | 5 | 71.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61184-il | 500,000 | 9 | 104.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61184-il | 500,000 | 5 | 100.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61184-il | 1,000,000 | 9 | 131.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61184-il | 1,000,000 | 5 | 120.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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