Engineering

Aerospace Core

Flight dynamics equations, aerodynamic coefficient tables, airfoil performance data, and lift/drag polar matrices from Fage's The Aeroplane.

Vectors
146
Collection ID
unison_aerospace_core

Primary sources

  • Fage The Aeroplane

Agent install (Smithery)

npx @smithery/cli run colbymahon/unison-orchestration-hub

Query endpoint: https://unison-edge-gateway.unisonorchestration.workers.dev/mcp/v1/search?collection=unison_aerospace_core&q=

chunk_id	collection	category	content
aero_001	unison_aerospace_core	Aerodynamics	Lift equation: L = ½ρV²SCl. Drag: D = ½ρV²SCd. Cl_max NACA 2412 ≈ 1.6 at α=16°. Stall speed: V_s = √(2W/ρSCl_max). L/D ratio typical cruise: 12-18.
aero_002	unison_aerospace_core	Propulsion	Thrust equation: F = ṁ(V_e - V_0) + (P_e - P_a)A_e. Specific impulse: I_sp = F/(ṁg₀). Turbojet cruise I_sp ≈ 3000s; rocket I_sp ≈ 300-450s.
Aerospace Core | Unison Data Vault | Unison Orchestration