Complete

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Complete Project

The purpose of the complete project is to further refine the airplane design. The user simply enters the information that describes the general configuration of the airplane, stemming from either the data aquired from the basic project, or from a previously developed design.

	Weight
	Propulsion
	Geometry
	Aerodynamics

Weight

Weight configuration :

	We = empty weight
	Pilot
	Passenger
	Baggage (freight)
	Fuel (capacity)

Propulsion

Propulsion configuration :

	Configuration
	Engine
	Propeller = propeller type
	Drive
	Blades = number of blades
	Cowling
	Consumption
	SFC = specific fuel consumption
	hp = nominal horse power
	Dp = prop diameter
	rpm = propulsion revolution
	Ratio

Geometry

Configuration of the design geometry :

Configuration:

Structure

Wing

Seating

Gear

Float ( if needed )

Wing:

S = surface

b = wing span

Horizontal tail unit :

Sh = horizontal tail surface

bh = horizontal tail span

Lh = horizontal tail arm

Vertical tail unit :

Sv =vertical tail surface

bv = vertical tail span

Lv= vertical tail arm

Fuselage:

Lf = fuselage length

Swet = wetted area

Aerodynamics

Configuration of the design aerodynamic:

	Aerodynamic Airfoil
	Flaps
	Wing
	Empennage Assembly
	Surface
	Structure
	Cabin
	Fairing
	Cowling
	Gear
	CLmax = maximum lift coefficient
	CLmaxf = maximum lift coefficient with flaps
	Cf = friction coefficient
	K = wing efficiency factor

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