FX 62-K-153/20 AIRFOIL (fx62k153-il)
FX 62-K-153/20 AIRFOIL - Wortmann FX 62-K-153/20 airfoil
| Details | Dat file | Parser | |
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(fx62k153-il) FX 62-K-153/20 AIRFOIL Wortmann FX 62-K-153/20 airfoil Max thickness 15.3% at 40.2% chord. Max camber 4.1% at 62.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
FX 62-K-153/20 AIRFOIL
49. 49.
0.0000000 0.0000000
0.0010200 0.0071100
0.0042200 0.0132500
0.0096000 0.0197400
0.0170200 0.0264300
0.0265000 0.0334400
0.0380200 0.0404900
0.0515800 0.0475500
0.0669400 0.0545300
0.0842200 0.0614200
0.1033000 0.0681500
0.1240300 0.0746700
0.1464300 0.0809000
0.1703700 0.0868800
0.1955800 0.0922000
0.2222100 0.0971200
0.2499800 0.1015600
0.2789100 0.1054600
0.3086100 0.1087900
0.3393300 0.1115100
0.3705600 0.1133100
0.4024300 0.1144800
0.4346900 0.1149400
0.4673300 0.1146300
0.4999700 0.1135600
0.5327400 0.1116700
0.5652500 0.1089900
0.5975000 0.1054800
0.6293800 0.1011100
0.6607400 0.0958400
0.6913300 0.0896800
0.7211500 0.0827800
0.7499501 0.0754100
0.7777300 0.0679000
0.8043500 0.0605300
0.8297000 0.0534300
0.8535000 0.0466900
0.8759000 0.0403400
0.8964400 0.0344200
0.9157100 0.0289000
0.9329900 0.0238200
0.9484800 0.0191500
0.9619200 0.0148800
0.9734400 0.0110000
0.9829100 0.0075500
0.9903400 0.0047100
0.9957100 0.0024000
0.9989100 0.0007300
1.0000000 0.0000000
0.0000000 0.0000000
0.0010200 -.0016600
0.0042200 -.0047800
0.0096000 -.0078500
0.0170200 -.0108200
0.0265000 -.0137100
0.0380200 -.0164500
0.0515800 -.0190300
0.0669400 -.0214900
0.0842200 -.0238500
0.1033000 -.0261100
0.1240300 -.0282600
0.1464300 -.0302600
0.1703700 -.0321200
0.1955800 -.0338200
0.2222100 -.0353300
0.2499800 -.0366000
0.2789100 -.0376300
0.3086100 -.0383300
0.3393300 -.0387000
0.3705600 -.0386800
0.4024300 -.0382500
0.4346900 -.0373400
0.4673300 -.0359200
0.4999700 -.0339000
0.5327400 -.0312600
0.5652500 -.0279700
0.5975000 -.0240400
0.6293800 -.0194700
0.6607400 -.0144300
0.6913300 -.0091400
0.7211500 -.0039900
0.7499501 0.0006800
0.7777300 0.0046000
0.8043500 0.0077200
0.8297000 0.0100400
0.8535000 0.0116400
0.8759000 0.0125500
0.8964400 0.0128400
0.9157100 0.0125700
0.9329900 0.0118100
0.9484800 0.0106000
0.9619200 0.0090300
0.9734400 0.0071900
0.9829100 0.0052200
0.9903400 0.0035000
0.9957100 0.0018600
0.9989100 0.0005100
1.0000000 0.0000000
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Polars for FX 62-K-153/20 AIRFOIL (fx62k153-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx62k153-il | 50,000 | 9 | 26.9 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx62k153-il | 50,000 | 5 | 23 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx62k153-il | 100,000 | 9 | 45.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx62k153-il | 100,000 | 5 | 44.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx62k153-il | 200,000 | 9 | 77.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx62k153-il | 200,000 | 5 | 79.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx62k153-il | 500,000 | 9 | 124.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx62k153-il | 500,000 | 5 | 122.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx62k153-il | 1,000,000 | 9 | 161.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx62k153-il | 1,000,000 | 5 | 151.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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