FX 60-177 AIRFOIL (fx60177-il)
FX 60-177 AIRFOIL - Wortmann FX 60-177 airfoil
| Details | Dat file | Parser | |
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(fx60177-il) FX 60-177 AIRFOIL Wortmann FX 60-177 airfoil Max thickness 17.7% at 37.1% chord. Max camber 2.7% at 77.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
FX 60-177 AIRFOIL
49. 49.
0.0000000 0.0000000
0.0010200 0.0098000
0.0042200 0.0178700
0.0096000 0.0257800
0.0170200 0.0339800
0.0265000 0.0417600
0.0380200 0.0497100
0.0515800 0.0572900
0.0669400 0.0646800
0.0842200 0.0715300
0.1033000 0.0780000
0.1240300 0.0837700
0.1464300 0.0891600
0.1703700 0.0937800
0.1955800 0.0980100
0.2222100 0.1014500
0.2499800 0.1044900
0.2780100 0.1067700
0.3086100 0.1086800
0.3393300 0.1098400
0.3705600 0.1105900
0.4024300 0.1106200
0.4346900 0.1102300
0.4673300 0.1091200
0.4999700 0.1075900
0.5327400 0.1054700
0.5652500 0.1029200
0.5975000 0.0996800
0.6293800 0.0960200
0.6607400 0.0917200
0.6913300 0.0869900
0.7211500 0.0817500
0.7499501 0.0761300
0.7777300 0.0702000
0.8043500 0.0640000
0.8297000 0.0576200
0.8535000 0.0511600
0.8759000 0.0446900
0.8964400 0.0383500
0.9157100 0.0323200
0.9329900 0.0264700
0.9484800 0.0210400
0.9619200 0.0161200
0.9734400 0.0116700
0.9829100 0.0077700
0.9903400 0.0046100
0.9957100 0.0022100
0.9989100 0.0006800
1.0000000 0.0000000
0.0000000 0.0000000
0.0010200 -.0015400
0.0042200 -.0055600
0.0096000 -.0099700
0.0170200 -.0145900
0.0265000 -.0194000
0.0380200 -.0240800
0.0515800 -.0288200
0.0669400 -.0335200
0.0842200 -.0380600
0.1033000 -.0423400
0.1240300 -.0464200
0.1464300 -.0501500
0.1703700 -.0536900
0.1955800 -.0568300
0.2222100 -.0597100
0.2499800 -.0620400
0.2780100 -.0640400
0.3086100 -.0654400
0.3393300 -.0663500
0.3705600 -.0666300
0.4024300 -.0664700
0.4346900 -.0656300
0.4673300 -.0643200
0.4999700 -.0622700
0.5327400 -.0596100
0.5652500 -.0561100
0.5975000 -.0519700
0.6293800 -.0469400
0.6607400 -.0413600
0.6913300 -.0351700
0.7211500 -.0287200
0.7499501 -.0220900
0.7777300 -.0157500
0.8043500 -.0098200
0.8297000 -.0046900
0.8535000 -.0003200
0.8759000 0.0030900
0.8964400 0.0056500
0.9157100 0.0073700
0.9329900 0.0082700
0.9484800 0.0084100
0.9619200 0.0078600
0.9734400 0.0067200
0.9829100 0.0051700
0.9903400 0.0034800
0.9957100 0.0018500
0.9989100 0.0006400
1.0000000 0.0000000
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Polars for FX 60-177 AIRFOIL (fx60177-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx60177-il | 50,000 | 9 | 24.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60177-il | 50,000 | 5 | 25 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60177-il | 100,000 | 9 | 40.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60177-il | 100,000 | 5 | 37.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60177-il | 200,000 | 9 | 49.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60177-il | 200,000 | 5 | 53.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60177-il | 500,000 | 9 | 81.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60177-il | 500,000 | 5 | 74.6 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60177-il | 1,000,000 | 9 | 105.5 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60177-il | 1,000,000 | 5 | 85.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||