GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il)
GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL - Gottingen 187 (Schatte-Lanz 2U10) airfoil
| Details | Dat file | Parser | |
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(goe187-il) GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL Gottingen 187 (Schatte-Lanz 2U10) airfoil Max thickness 8.3% at 30% chord. Max camber 4.8% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125200 0.0204900
0.0250300 0.0315800
0.0500400 0.0465600
0.0750400 0.0560400
0.1000500 0.0643200
0.1500600 0.0759800
0.2000700 0.0842400
0.3000700 0.0897600
0.4000700 0.0873800
0.5000600 0.0807000
0.6000600 0.0689200
0.7000400 0.0544400
0.8000300 0.0387600
0.9000200 0.0214800
0.9500100 0.0125400
1.0000000 0.0025000
0.0000000 0.0000000
0.0125000 -.0017100
0.0250000 -.0006200
0.0500000 0.0011100
0.0750000 0.0021800
0.1000000 0.0029900
0.1500000 0.0042800
0.2000000 0.0053400
0.3000100 0.0069600
0.4000100 0.0079800
0.5000100 0.0079000
0.6000100 0.0067200
0.7000000 0.0055400
0.8000000 0.0032600
0.9000000 -.0007200
0.9500000 -.0024600
1.0000000 -.0025000
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Polars for GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe187-il | 50,000 | 9 | 31.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe187-il | 50,000 | 5 | 40.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe187-il | 100,000 | 9 | 53.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe187-il | 100,000 | 5 | 58.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe187-il | 200,000 | 9 | 74.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe187-il | 200,000 | 5 | 76.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe187-il | 500,000 | 9 | 100.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe187-il | 500,000 | 5 | 98.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe187-il | 1,000,000 | 9 | 118.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe187-il | 1,000,000 | 5 | 112.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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