Airfoil DetailsNACA 63012A AIRFOIL

Properties

NACA 63012A AIRFOIL

n63012a

Thickness

12.0%

Max t/c Loc

35.4%

Camber

0.0%

Max Camber Loc

12.5%

Simulation Conditions

Mach

0.00

Ncrit

Model Size

large

Plot Type

Ncrit

Reynolds Numbers

Kulfan Parameters

{
  "n1": 0.5,
  "n2": 1,
  "TE_thickness": 0.0005010355179925624,
  "leading_edge_weight": 9.848071304757248e-16,
  "upper_weights": [
    0.13534288986289264,
    0.13458747201845842,
    0.17197248950798905,
    0.14603585268306762,
    0.18418192416833332,
    0.12602037954657413,
    0.1328306473847963,
    0.11934400460902901
  ],
  "lower_weights": [
    -0.13534288986289278,
    -0.1345874720184581,
    -0.17197248950798877,
    -0.14603585268306774,
    -0.18418192416833457,
    -0.12602037954657153,
    -0.1328306473847992,
    -0.119344004609027
  ]
}

Airfoil Geometry

Performance Metrics

Active Scales:0 Reynolds Active

Aerodynamic Analysis: Peter Sharpe's NeuralFoil

The performance data shown here is generated using NeuralFoil, an advanced aerodynamic engine developed by Peter Sharpe as part of the AeroSandbox project.

How it Works

NeuralFoil is a deep neural network trained on millions of XFoil simulations. It replicates the viscid-inviscid coupled panel method results with near-instantaneous speed, providing critical design data including \\(C_l\\), \\(C_d\\), and \\(C_m\\).

The Database Sweep

This database was generated using a high-fidelity model size (large) at incompressible speeds (Mach 0.00) and a critical N-factor of 9.0. The sweep covers a wide range of Reynolds numbers to ensure accuracy across scales.

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Aircraft Usage

Found in UIUC Database

0Known Applications

No specific aircraft mappings found for "n63012a" in the current database.

Kulfan Parameters