GOE 504 AIRFOIL (goe504-il)
GOE 504 AIRFOIL - Gottingen 504 airfoil
| Details | Dat file | Parser | |
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(goe504-il) GOE 504 AIRFOIL Gottingen 504 airfoil Max thickness 18% at 29.2% chord. Max camber 5.4% at 39.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 504 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0112300 0.0231200
0.0229500 0.0372600
0.0467000 0.0600700
0.0706900 0.0783900
0.0949000 0.0927200
0.1437400 0.1139100
0.1929800 0.1276100
0.2922400 0.1410700
0.3922200 0.1415700
0.4927400 0.1321000
0.5936700 0.1151500
0.6949300 0.0922200
0.7964100 0.0653000
0.8981100 0.0344000
0.9490500 0.0172000
1.0000000 0.0000000
0.0000000 0.0000000
0.0132900 -.0142700
0.0260500 -.0190700
0.0515000 -.0271700
0.0767800 -.0322800
0.1019800 -.0358900
0.1522600 -.0411300
0.2023300 -.0423700
0.3021100 -.0383800
0.4018100 -.0329000
0.5015100 -.0274200
0.6012100 -.0219300
0.7009100 -.0164500
0.8006000 -.0109700
0.9003000 -.0054800
0.9501500 -.0027400
1.0000000 0.0000000
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Polars for GOE 504 AIRFOIL (goe504-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe504-il | 50,000 | 9 | 3.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe504-il | 50,000 | 5 | 13.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe504-il | 100,000 | 9 | 34.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe504-il | 100,000 | 5 | 43.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe504-il | 200,000 | 9 | 66.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe504-il | 200,000 | 5 | 62.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe504-il | 500,000 | 9 | 91.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe504-il | 500,000 | 5 | 85.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe504-il | 1,000,000 | 9 | 114.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe504-il | 1,000,000 | 5 | 104.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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