FX 38-153 AIRFOIL (fx38153-il)
FX 38-153 AIRFOIL - Wortmann FX 38-153 airfoil
| Details | Dat file | Parser | |
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(fx38153-il) FX 38-153 AIRFOIL Wortmann FX 38-153 airfoil Max thickness 15.5% at 43.5% chord. Max camber 2.1% at 80.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
FX 38-153 AIRFOIL
49. 49.
0.0000000 0.0000000
0.0010200 0.0064500
0.0042200 0.0134900
0.0096000 0.0191400
0.0170200 0.0263000
0.0265000 0.0327000
0.0380200 0.0397500
0.0515800 0.0461100
0.0669400 0.0526600
0.0842200 0.0584600
0.1033000 0.0642400
0.1240300 0.0692900
0.1464300 0.0742600
0.1703400 0.0785300
0.1955800 0.0826600
0.2222100 0.0861100
0.2499800 0.0893200
0.2789100 0.0918200
0.3086100 0.0940200
0.3393300 0.0955100
0.3705600 0.0967000
0.4024300 0.0971800
0.4346900 0.0973900
0.4673300 0.0969500
0.4999700 0.0961800
0.5327400 0.0948200
0.5652500 0.0931100
0.5975000 0.0908300
0.6293800 0.0882100
0.6607400 0.0850300
0.6913300 0.0814800
0.7211500 0.0773200
0.7499501 0.0727200
0.7777300 0.0675900
0.8043500 0.0620300
0.8297000 0.0559600
0.8535000 0.0495800
0.8759000 0.0429100
0.8964400 0.0362800
0.9157100 0.0298800
0.9329900 0.0239500
0.9484800 0.0185600
0.9619200 0.0138300
0.9734400 0.0097000
0.9829100 0.0062400
0.9903400 0.0035400
0.9957100 0.0015900
0.9989100 0.0004200
1.0000000 0.0000000
0.0000000 0.0000000
0.0010200 -.0024500
0.0042200 -.0051900
0.0096000 -.0091000
0.0170200 -.0122800
0.0265000 -.0162900
0.0380200 -.0196200
0.0515800 -.0234800
0.0669400 -.0268700
0.0842200 -.0306300
0.1033000 -.0338600
0.1240300 -.0373500
0.1464300 -.0403400
0.1703400 -.0434500
0.1955800 -.0461000
0.2222100 -.0487100
0.2499800 -.0508800
0.2789100 -.0530300
0.3086100 -.0546600
0.3393300 -.0561800
0.3705600 -.0571200
0.4024300 -.0578500
0.4346900 -.0580300
0.4673300 -.0579600
0.4999700 -.0572700
0.5327400 -.0562200
0.5652500 -.0545800
0.5975000 -.0525400
0.6293800 -.0497900
0.6607400 -.0464000
0.6913300 -.0421400
0.7211500 -.0371600
0.7499501 -.0314100
0.7777300 -.0253500
0.8043500 -.0192600
0.8297000 -.0135400
0.8535000 -.0083600
0.8759000 -.0040600
0.8964400 -.0005900
0.9157100 0.0020300
0.9329900 0.0038100
0.9484800 0.0047900
0.9619200 0.0050300
0.9734400 0.0046100
0.9829100 0.0037100
0.9903400 0.0025900
0.9957100 0.0014200
0.9989100 0.0005100
1.0000000 0.0000000
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Polars for FX 38-153 AIRFOIL (fx38153-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx38153-il | 50,000 | 9 | 31.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx38153-il | 50,000 | 5 | 26.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx38153-il | 100,000 | 9 | 46.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx38153-il | 100,000 | 5 | 36.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx38153-il | 200,000 | 9 | 46.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx38153-il | 200,000 | 5 | 47.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx38153-il | 500,000 | 9 | 63.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx38153-il | 500,000 | 5 | 60.8 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx38153-il | 1,000,000 | 9 | 91.5 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx38153-il | 1,000,000 | 5 | 64.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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