GOE 387 AIRFOIL Airfoil
goe387Properties
Plot Type
Ncrit
Reynolds Numbers
Kulfan Parameters
Airfoil Geometry
GOE 387 AIRFOIL at a glance
At a Reynolds number of 1,000,000 the GOE 387 AIRFOIL reaches a maximum lift coefficient of 1.71 at 16.0° angle of attack, a best lift-to-drag ratio of 128 at Cl 1.17 (5.5°), and a minimum drag coefficient of 0.0071. It carries zero lift at -5.1°.
| Reynolds number | 200,000 | 1,000,000 | 5,000,000 |
|---|---|---|---|
| Max Clthe stall peak | 1.61 | 1.71 | 1.92 |
| at alphaangle of attack it occurs at | 14.5° | 16.0° | 18.0° |
| Best L/Dhighest lift-to-drag ratio | 72 | 128 | 182 |
| at Cllift coefficient it occurs at |
Performance Metrics
These curves are computed with NeuralFoil, a neural network trained on XFOIL, from a stored sweep across Reynolds number, Ncrit and angle of attack. How the polars are computed, and where they stop being trustworthy →
Run it at your Reynolds number
The curves above are a stored sweep at fixed Reynolds numbers. Enter the one your chord and speed actually give and NeuralFoil computes that polar now, onto this chart.
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Aircraft Usage
Found in UIUC Database
Aircraft recorded with two or more sections have a page of their own. All recorded aircraft
Sections like the GOE 387 AIRFOIL
The five closest shapes in the library, by maximum thickness and camber and where along the chord each falls.
- GOE 654 AIRFOIL14.5% thick · 5.2% camber
- GOE 615 AIRFOIL13.8% thick · 5.6% camber
- GOE 481A AIRFOIL15.3% thick · 5.5% camber
- GOE 624 AIRFOIL16.0% thick · 5.2% camber
- GOE 398 AIRFOIL13.9% thick · 4.9% camber
Ranked on geometry alone, from the stored CST parameters — no polar is consulted, so a section that sits close here can still behave differently at the Reynolds number you fly. A near-symmetric section is matched on thickness and its distribution only: with no camber to speak of, where its camber peaks is rounding error rather than shape.