AeroLab 3Dvortex-lattice aircraft & Barrowman rocket laboratory

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α2.0°

V∞50 m/s

Re–

Mach–

Portfolio

Forces & moments wind axes · whole aircraft

	VLM inviscid	+ viscous est.
C_L	–	–
C_D	–	–
L/D	–	–
C_m (pitch)	–	·
C_Y / C_l / C_n	–	·
Lift [kN]	–	–
Drag [kN]	–	–

Spanwise loading c_l·c / c_ref vs 2y/b

wing h-stabcanard elliptic ref cl > cl_max

Lift curve & drag polar VLM sweep + viscous drag

C_L(α) C_L vs C_D current point

Stability & trim about CG

Level flight at current mass & altitude fluid

Static aerodynamics Barrowman · ref = base area

	CNα [/rad]	CP from nose

Stability diagram CP vs CG along body

CP (centre of pressure) CG (centre of gravity)

Drag build-up at current V∞ · α = 0

Flight estimate 1-DOF vertical · sea-level ρ

Entry state live · scrub or play

Entry corridor altitude vs velocity

trajectory peak heating peak g now

Heating & loads vs time

stag. heat flux q̇ deceleration [g]

Altitude & speed vs time

altitude velocity

Peaks & totals whole trajectory

Freestream & scales

Solver internals