FX 60-157 AIRFOIL (fx60157-il)
FX 60-157 AIRFOIL - Wortmann FX 60-157 airfoil
| Details | Dat file | Parser | |
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(fx60157-il) FX 60-157 AIRFOIL Wortmann FX 60-157 airfoil Max thickness 15.7% at 40.2% chord. Max camber 2.7% at 75% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
FX 60-157 AIRFOIL
49. 49.
0.0000000 0.0000000
0.0010200 0.0084700
0.0042200 0.0158200
0.0096000 0.0218300
0.0170200 0.0293000
0.0265000 0.0361800
0.0380200 0.0438000
0.0515800 0.0506800
0.0669400 0.0577500
0.0842200 0.0639700
0.1033000 0.0701900
0.1240300 0.0755600
0.1464300 0.0807500
0.1703700 0.0850900
0.1955800 0.0891700
0.2222100 0.0924700
0.2499800 0.0954500
0.2789100 0.0976900
0.3086100 0.0995500
0.3393300 0.1007100
0.3705600 0.1014800
0.4024300 0.1015100
0.4346900 0.1011600
0.4673300 0.1001300
0.4999700 0.0987500
0.5327400 0.0967600
0.5652500 0.0943800
0.5975000 0.0913900
0.6293800 0.0880100
0.6607400 0.0840000
0.6913300 0.0796100
0.7211500 0.0747100
0.7499501 0.0694700
0.7777300 0.0638400
0.8043500 0.0580300
0.8297000 0.0520000
0.8535000 0.0459300
0.8759000 0.0398800
0.8964400 0.0340400
0.9157100 0.0284200
0.9329900 0.0231600
0.9484800 0.0182900
0.9619200 0.0138900
0.9734400 0.0099700
0.9829100 0.0065800
0.9903400 0.0038600
0.9957100 0.0018400
0.9989100 0.0005600
1.0000000 0.0000000
0.0000000 0.0000000
0.0010200 -.0022200
0.0042200 -.0058500
0.0096000 -.0103200
0.0170200 -.0140300
0.0265000 -.0182500
0.0380200 -.0218300
0.0515800 -.0257500
0.0669400 -.0291800
0.0842200 -.0329600
0.1033000 -.0362100
0.1240300 -.0396600
0.1464300 -.0425700
0.1703700 -.0455700
0.1955800 -.0479700
0.2222100 -.0503600
0.2499800 -.0520600
0.2789100 -.0536800
0.3086100 -.0546200
0.3393300 -.0553700
0.3705600 -.0551400
0.4024300 -.0552200
0.4346900 -.0543800
0.4673300 -.0532300
0.4999700 -.0513900
0.5327400 -.0491400
0.5652500 -.0460100
0.5975000 -.0422900
0.6293800 -.0376900
0.6607400 -.0324800
0.6913300 -.0267200
0.7211500 -.0209000
0.7499501 -.0151400
0.7777300 -.0099200
0.8043500 -.0052700
0.8297000 -.0013900
0.8535000 0.0017700
0.8759000 0.0041700
0.8964400 0.0058800
0.9157100 0.0069100
0.9329900 0.0073300
0.9484800 0.0071700
0.9619200 0.0065200
0.9734400 0.0054300
0.9829100 0.0040700
0.9903400 0.0026700
0.9957100 0.0013700
0.9989100 0.0004400
1.0000000 0.0000000
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Polars for FX 60-157 AIRFOIL (fx60157-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx60157-il | 50,000 | 9 | 28.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60157-il | 50,000 | 5 | 28.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60157-il | 100,000 | 9 | 46.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60157-il | 100,000 | 5 | 41.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60157-il | 200,000 | 9 | 56.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60157-il | 200,000 | 5 | 57.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60157-il | 500,000 | 9 | 81.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60157-il | 500,000 | 5 | 70 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60157-il | 1,000,000 | 9 | 95.8 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60157-il | 1,000,000 | 5 | 72.8 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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