Design ListDesign_List 

Other Available Tabs

Detail TabDetail_Tab 

Drag Breakdown TabDrag_Breakdown_Tab 

Performance TabPerformance_Tab 

Power Required TabPower_Required_Tab 

Lift to Drag Ratio TabLift_to_Drag_Ratio_Tab 


This tab displays a plan view of a design item and provides tools to create and modify a design item. The view provided varies according to the selected design item. The following design items and views are provided;


Wing, Tail

A plan view of half of the wing or tail and end view is plotted in a scrollable window   The wing or tail end view has been simplified to speed up screen redraws. If different airfoil sections are selected for the root and tip chords, only the root chord section will be used for the plotting of each rib section.  Allowing the transition of airfoil sections along the span would reduce the plotting speed to an unbearable speed. All dimensions are based on the span of the item.

Fuselage Side, Top or Bottom

An elevation view is provided in a scrollable window. The nose or firewall position is at the left most extremity of the item (referred to as Datum 1) and the tail or fuselage end is at the right most extremity (referred to as Datum 2). All dimensions are based on the length of the item.

Fuselage Former

An elevation view is provided in a scrollable window. The left side is at the left most extremity of the item (referred to as Datum 1) and the right side of the former is at the right most extremity (referred to as Datum 2). All dimensions are based on the width of the item.


The plot may be increased or decreased in size by clicking on the magnify or reduce buttons in the tool bar running along the bottom of the screen. The plot may also be scrolled up and down or left and right so as to position the plot as required. 


A design item is input by either using the mouse or by entering the coordinates of the design item through the keyboard. The position of the mouse pointer is shown as a dimension based on the distance from the top edge point of the left most coordinate of the design item. Coordinates of a design item are entered as pairs, ie; upper coordinate (top edge) first then lower coordinate (lower edge). Typically a simple tapered wing will only need two coordinate pairs. One pair for the root of the wing and one pair for the tip of the wing. If you wish to design an elliptical wing , a number of coordinate pairs will need to be entered, with a close distribution of coordinate pairs at the tip to capture the rounded tip shape.

The CADCAD interface provides the capability to select coordinate points with the mouse. Once selected a coordinate pair can be moved about or stretched apart to alter the shape of a wing, tail or fuselage component.


Items which can be changed on this screen are;


Measurement Units

Select or click on the dropdown list of measurement units to change. When the units are changed all dimensions are recalculated for the selected units.

Root Airfoil

Select or click on the dropdown list of airfoils to change the airfoil at the root of the wing or tail design.

Tip Airfoil

Select or click on the dropdown list of airfoils to change the airfoil at the tip of the wing or tail design.

Span or Length

Enter a new value in this box to change the span or fuselage length or former width. Next to this box is a button called . This is used to select the type of scaling applied when the span, length or width is changed. 

An Option button is provided to allow one of two options;

1. To scale the design and maintain the Aspect Ratio. The design will be scaled proportionally.

2. Do not scale design. Span or length will be increased however new points must be either deleted if the span is reduced or added if the span is increased.


No. of Ribs

Enter a value in this box to change the number of ribs. Click on the Redraw Design Toolbar button for this to take effect. This will cause the wing or tail design to be redrawn and the rib lengths recalculated.


The Windows Calculator can be accessed from the Tool Menu or by pressing the function key F5 to perform scaling calculations as required.


Whenever an item is modified Winfoil will recalculate the following;


Wing, Tail

Area, Aspect Ratio, Mean Aerodynamic Centre (25% chord position) and rib lengths. The mean aerodynamic chord position (25%) can be used to determine tail sizes for adequate stability also it can be used as a guide to positioning the centre of gravity for conventional configured aircraft (non-canard). This is very useful for aircraft with swept wings. A safe centre of gravity range is typically 15% to 33% of the Mean Aerodynamic Chord of the wing (Assuming an adequate horizontal tail area has been selected). Positions further aft or forward cannot be confirmed as being safe without a full stability analysis.

Fuselage Side, Top or Bottom

Area

Fuselage Former

Area


Other capabilities provided in this screen;

Graph of Reynolds number distribution along the semi span of a wing or tail for a range of selected speeds in air or water. This could highlight problems with sharply tapered wings which could be prone to tip stalling. A checking facility is also provided to verify airfoil selection with aerodynamic data. 

Spar Design for Wings and tails



Design CAD Tool Bar FunctionsWING_CAD_TOOL_BAR_FUNCTIONS 

How to design a wing in the Design CAD ScreenHOW_TO_DESIGN_A_WING_IN_WING_CAD