Saqr ConsultingDesign sheets
Saqr Consulting

Constraint Diagram & Design Point

Stall · cruise · climb · launch · turn — and what is left
Sheet 06
A file you keep, not an account. Nothing is stored on this site.
The aircraft
g
From Sheet 05 if you built a budget. This sheet does not size the mass, it sizes the wing and the motor that mass needs.
AR
CL
Whole-wing figures, both from Sheet 01. The lift coefficient is the section value already reduced for a finite wing.
CD0
Same list as Sheet 04, so the two sheets describe the same aeroplane. Sheet 07 builds this up component by component and sends the result here.
e
Oswald span efficiency: the penalty a real wing pays against an elliptical one. Compiled from planform practice, not measured — taper, washout and how the wing meets the fuselage all move it.
ηp
These multiply. A cruise propeller figure is used at every speed on this chart, which flatters the launch and climb boundaries — see the note under the diagram.
What it has to do
km/h
The hard one. It sets the largest wing loading you are allowed, and so the right-hand edge of everything. Pick it from the field you fly off and your own reflexes, not from a wish.
km/h
A useful cruise is around 1.4 times the stall speed. Faster costs power as the cube of speed.
m/s
2–3 gentle, 4–6 sport, 8–12 aerobatic. This is usually the boundary that decides the motor.
m of roll
Distance from standing to lift-off. Grass roughly doubles what tarmac needs; this boundary assumes a clean hard surface.
° bank
—
A flat floor from build practice rather than from the drag polar. It catches what the equations miss: control authority, headroom, and the fact that nobody enjoys an aeroplane sized exactly to its own arithmetic.
Air
m ASL
°C
% RH
Thin air moves every boundary on the chart at once: the stall limit left, the power boundaries up. Leave the temperature blank for the standard atmosphere.
Design point
—
Set a mass and the requirements on the left.

What this sheet works out

Constraint diagram

Constraint diagram: power loading against wing loading Each performance requirement is drawn as a boundary. The shaded region satisfies all of them at once, and the design point sits at its corner.

What each requirement demands at the design point

Where people go wrong

The errors this method actually invites, and what it does about each. Every one of them is already a warning somewhere — in a note that appears when your own figures trip it, in the scope statement, or in the equations behind the page. Collected here so you can read them before you need them.

Reading the design point as the best aeroplane. It is the smallest wing the brief allows, which is a convention rather than a law. A larger wing usually flies on less power, and the sheet reports where the envelope is lowest so you can see the trade you are declining.

Dismissing the practice floor because it is not derived. It is compiled from build practice and it catches what a cruise-and-climb calculation cannot see — control authority and headroom. It is the boundary most worth overruling, and the one to overrule deliberately rather than by accident.

Trusting the climb and launch boundaries. A single cruise propeller efficiency is applied at every speed, so those two boundaries sit lower than the truth. That is the optimistic direction, and it is the one that costs you a motor.

Sizing the wing from a mass the wing changes. The method assumes the mass is known while the mass depends on the wing being sized. Run Sheet 05 with the answer and come back; two passes usually settle it.