GOE 430 AIRFOIL (goe430-il)
GOE 430 AIRFOIL - Gottingen 430 airfoil
| Details | Dat file | Parser | |
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(goe430-il) GOE 430 AIRFOIL Gottingen 430 airfoil Max thickness 13.4% at 29.5% chord. Max camber 4.8% at 49.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 430 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0116000 0.0205100
0.0236100 0.0318300
0.0478500 0.0491000
0.0723500 0.0604700
0.0969300 0.0701500
0.1463100 0.0842100
0.1959100 0.0933800
0.2953400 0.1064400
0.3952900 0.1075100
0.4955200 0.1022000
0.5960200 0.0909100
0.6967000 0.0753200
0.7976200 0.0543400
0.8945000 0.0299500
0.9493200 0.0155800
1.0000000 0.0011000
0.0000000 0.0000000
0.0133800 -.0200100
0.0262100 -.0275500
0.0514900 -.0340400
0.0766500 -.0377400
0.1017200 -.0393400
0.1516800 -.0382600
0.2015800 -.0360700
0.3011700 -.0268100
0.4007300 -.0165500
0.5002300 -.0051900
0.5998000 0.0045700
0.6994600 0.0122400
0.7994200 0.0133100
0.8996000 0.0091000
0.9497899 0.0048000
1.0000000 -.0011000
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Polars for GOE 430 AIRFOIL (goe430-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe430-il | 50,000 | 9 | 30.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe430-il | 50,000 | 5 | 36.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe430-il | 100,000 | 9 | 59.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe430-il | 100,000 | 5 | 60.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe430-il | 200,000 | 9 | 83.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe430-il | 200,000 | 5 | 79.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe430-il | 500,000 | 9 | 111.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe430-il | 500,000 | 5 | 96.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe430-il | 1,000,000 | 9 | 125.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe430-il | 1,000,000 | 5 | 104.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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