GOE 553 AIRFOIL (goe553-il)
GOE 553 AIRFOIL - Gottingen 553 airfoil
| Details | Dat file | Parser | |
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(goe553-il) GOE 553 AIRFOIL Gottingen 553 airfoil Max thickness 13.7% at 29.6% chord. Max camber 4.7% at 39.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 553 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0115800 0.0288700
0.0237000 0.0407600
0.0481600 0.0575400
0.0727300 0.0708300
0.0973700 0.0821200
0.1469100 0.0967000
0.1965800 0.1067900
0.2963400 0.1144800
0.3964400 0.1111900
0.4967900 0.1004000
0.5973200 0.0836100
0.6979100 0.0653300
0.7985399 0.0455500
0.8992400 0.0237800
0.9496000 0.0123900
1.0000000 0.0000000
0.0000000 0.0000000
0.0129500 -.0140900
0.0255700 -.0176800
0.0506700 -.0208800
0.0757400 -.0230800
0.1007600 -.0237800
0.1507900 -.0246700
0.2007900 -.0245700
0.3007200 -.0223800
0.4005700 -.0176800
0.5003200 -.0099900
0.6000600 -.0018000
0.6998600 0.0044000
0.7997700 0.0070900
0.8998300 0.0052900
0.9499100 0.0029000
1.0000000 0.0000000
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Polars for GOE 553 AIRFOIL (goe553-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe553-il | 50,000 | 9 | 11.2 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe553-il | 50,000 | 5 | 30.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe553-il | 100,000 | 9 | 45.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe553-il | 100,000 | 5 | 54.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe553-il | 200,000 | 9 | 73 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe553-il | 200,000 | 5 | 75 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe553-il | 500,000 | 9 | 105.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe553-il | 500,000 | 5 | 102.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe553-il | 1,000,000 | 9 | 130.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe553-il | 1,000,000 | 5 | 122.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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