GOE 702 AIRFOIL (goe702-il)
GOE 702 AIRFOIL - Gottingen 702 airfoil
| Details | Dat file | Parser | |
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(goe702-il) GOE 702 AIRFOIL Gottingen 702 airfoil Max thickness 16.6% at 19.4% chord. Max camber 5.1% at 39.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 702 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0109000 0.0310600
0.0226500 0.0456700
0.0466100 0.0659000
0.0708200 0.0811500
0.0951700 0.0939000
0.1441900 0.1129300
0.1935700 0.1249700
0.2931700 0.1326000
0.3935000 0.1262600
0.4941800 0.1129500
0.5952800 0.0916600
0.6965800 0.0663700
0.7979100 0.0405900
0.8991300 0.0168100
0.9495700 0.0084000
1.0000000 0.0000000
0.0000000 0.0000000
0.0136800 -.0228000
0.0265800 -.0306300
0.0519800 -.0383200
0.0771700 -.0420300
0.1022300 -.0432400
0.1522200 -.0431600
0.2021200 -.0410900
0.3016700 -.0324600
0.4012000 -.0233400
0.5008600 -.0167100
0.6006700 -.0130700
0.7005400 -.0104200
0.8004500 -.0087800
0.9002600 -.0051400
0.9501300 -.0025700
1.0000000 0.0000000
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Polars for GOE 702 AIRFOIL (goe702-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe702-il | 50,000 | 9 | 4.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe702-il | 50,000 | 5 | 20.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe702-il | 100,000 | 9 | 32 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe702-il | 100,000 | 5 | 43.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe702-il | 200,000 | 9 | 57.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe702-il | 200,000 | 5 | 61.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe702-il | 500,000 | 9 | 88.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe702-il | 500,000 | 5 | 89.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe702-il | 1,000,000 | 9 | 117.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe702-il | 1,000,000 | 5 | 116.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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