GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il)
GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL - Gottingen 188 (Schatte-Lanz 3U10) airfoil
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(goe188-il) GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL Gottingen 188 (Schatte-Lanz 3U10) airfoil Max thickness 8.9% at 30% chord. Max camber 4.3% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0212100
0.0250000 0.0309300
0.0500000 0.0441600
0.0750000 0.0545800
0.1000000 0.0632100
0.1500000 0.0750600
0.2000000 0.0829200
0.3000000 0.0886300
0.4000000 0.0870400
0.5000000 0.0809500
0.6000000 0.0693600
0.7000000 0.0549700
0.8000000 0.0388800
0.9000000 0.0233900
0.9500000 0.0150500
1.0000000 0.0050000
0.0000000 0.0000000
0.0125000 -.0010900
0.0250000 -.0010700
0.0500000 -.0010500
0.0750000 -.0010200
0.1000000 -.0009900
0.1500000 -.0009400
0.2000000 -.0008800
0.3000000 -.0007700
0.4000000 -.0006600
0.5000000 -.0005500
0.6000000 -.0004400
0.7000000 -.0003300
0.8000000 -.0002200
0.9000000 -.0001100
0.9500000 -.0000500
1.0000000 0.0000000
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Polars for GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe188-il | 50,000 | 9 | 31.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe188-il | 50,000 | 5 | 39.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe188-il | 100,000 | 9 | 51.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe188-il | 100,000 | 5 | 57.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe188-il | 200,000 | 9 | 71.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe188-il | 200,000 | 5 | 74.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe188-il | 500,000 | 9 | 98.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe188-il | 500,000 | 5 | 99 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe188-il | 1,000,000 | 9 | 119.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe188-il | 1,000,000 | 5 | 116.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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