GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il)
GOE 176 (ALBATROS 7020) AIRFOIL - Gottingen 176 (Albatros 7020) airfoil
| Details | Dat file | Parser | |
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(goe176-il) GOE 176 (ALBATROS 7020) AIRFOIL Gottingen 176 (Albatros 7020) airfoil Max thickness 10.3% at 19.8% chord. Max camber 5.6% at 39.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 176 (ALBATROS 7020) AIRFOIL
17. 17.
0.0000000 0.0000000
0.0121400 0.0220000
0.0244400 0.0343900
0.0492100 0.0487900
0.0739900 0.0625900
0.0988400 0.0718000
0.1486200 0.0854000
0.1984700 0.0949100
0.2983900 0.0994200
0.3984100 0.0987300
0.4985400 0.0904500
0.5987300 0.0783700
0.6989800 0.0630900
0.7992700 0.0452100
0.8995700 0.0264300
0.9497400 0.0161400
1.0000000 0.0011500
0.0000000 0.0000000
0.0126200 -.0072000
0.0251600 -.0098900
0.0501900 -.0132900
0.0752300 -.0153900
0.1002500 -.0156800
0.1502200 -.0136700
0.2001300 -.0082700
0.2999400 0.0038400
0.3998000 0.0124600
0.4997100 0.0178700
0.5997100 0.0180900
0.6924500 0.0158200
0.7998000 0.0125200
0.8998900 0.0065300
0.9499500 0.0032400
1.0000000 -.0011500
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Polars for GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe176-il | 50,000 | 9 | 30.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe176-il | 50,000 | 5 | 40.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe176-il | 100,000 | 9 | 56 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe176-il | 100,000 | 5 | 57.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe176-il | 200,000 | 9 | 73.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe176-il | 200,000 | 5 | 73.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe176-il | 500,000 | 9 | 99.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe176-il | 500,000 | 5 | 87 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe176-il | 1,000,000 | 9 | 113.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe176-il | 1,000,000 | 5 | 93.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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