AirfoilSimple00

calculates coefficients of lift and drag of 2d airfoil as function of angle of attack. Positive and negative stall angle of attack can be specified.

Scope/Calculation function

• estimate 2d airfoil characteristics as base of 3d wing characteristics estimation.

Short description of physical model/calculation method

• Coefficient of lift, Cl, and coefficient of drag, Cd, are calculated as function of angle of attack.
• Coefficient of drag, Cd is composed of friciton drag term and pressure drag term.
• Sudden loss of lift due to stall can be simulateed (by very simple model).
• Sudden increase of drag due to stall can be simulated (by very simple model).

Limitations/Assumptions of model

• Cl is linear function of angle of attack.
• Cdp, pressure drag coefficient, is calculated as power function of angle of attack.
• Compressibity effect is not taken into account, or neither Cl nor Cd are function of mach number.
• Viscossity effect is not taken into accountm, or neither Cl nor Cd are function of Raynolds number.
• Cdf, friction drag coefficient, is constant value.

Interface

Parameters

Read the descriptions on parameter window in model for details of each parameter. This section only covers parameters which requires descriptions by figures/drawings.

Usage

• fill following connectors:
• signalBus1.alpha
• signalBus2.Cl (can be left unconnected)
• signalBus2.Cd (can be left unconnected)
• set parameters in "Characteristics".

Warning/Causions

none

Demo models

***** under construction *****

Equations in details

***** under construction *****