Aircraft libraryAIRCRAFT DESIGNER / SCHEMA 1.1A

New aircraft concept

Define the engineering inputs that become the canonical simulation record.

Seeded from the documented Aquila referenceEvery value is visible below. Saving validates inputs; finalize separately from the version timeline.

Identity and configuration

Name the concept and identify the architecture being modeled.

Aircraft nameConfigurationPassenger countMaximum takeoff masskgDescription

Mass model

Component masses are reconciled into operating empty and takeoff mass.

Structural masskgBattery masskgPropulsion masskgAvionics masskgOther masskgPayloadkg

Battery and electrical

Pack capacity, usable window, discharge limit, and efficiencies.

Total capacitykWhUsable capacity%Nominal voltageVMaximum dischargekWReserve SOC%Battery efficiencyη

Propulsion

Installed motors, rotors, thrust, and conversion efficiencies.

Motor countRotor countPower per motorkWMaximum thrust per motorNRotor diametermAuxiliary powerkWMotor efficiencyηInverter efficiencyηPropeller efficiencyηHover figure of meritη

Aerodynamics

Wing and parasite-drag inputs used by model 0.2.

Wing aream²Aspect ratioZero-lift drag coefficientOswald efficiencyηCruise lift coefficientMaximum lift coefficientEquivalent frontal aream²Parasite drag coefficient

Reference environment

Explicit atmosphere and headwind assumptions saved with the design.

Air densitykg/m³Temperature°CHeadwindkm/hReference altitudem