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Aquila U-8

Exportable conceptual engineering record generated from the current local workspace.

Previewing the current canonical aircraft and saved mission.
A
AEROSIMEVTOL CONCEPT LAB
CONCEPTUAL ENGINEERING REPORT

Aquila U-8

Fictional Lift + Cruise reference concept for simulation model 0.2.

ConfigurationLift + Cruise
Revision1
ModelSimulation 0.2
GeneratedSep 8, 2026, 7:50 PM
LIMITED PURPOSE - CONCEPTUAL SIMULATION

Conceptual simulation only. Results are estimates based on simplified models and user-defined assumptions. They are not suitable for aircraft certification, flight authorization, safety decisions, or real-world aircraft operation without appropriate engineering validation.

01
AIRCRAFT OVERVIEW

Configuration and reconciled mass

Calculated takeoff mass600 kg
Operating empty mass420 kg
Payload180 kg
Declared MTOW600 kg
Passengers2
Mass definitionComponent-level
02
BATTERY

Energy storage

Total / usable capacity120 kWh / 90%
Battery mass / specific energy240 kg / 500 Wh/kg
Maximum discharge400 kW
Reserve SOC / efficiency20% / 96.0%
03
PROPULSION

Installed system

Motors / rotors8 / 8
Installed shaft power440 kW
Rotor diameter / total area1.75 m / 19.2 m²
Disk loading / thrust-weight31.2 kg/m² / 1.29
04
AERODYNAMICS

Reference geometry

Wing area / aspect ratio10.0 m² / 8.0
CD0 / Oswald efficiency0.035 / 0.80
Equivalent frontal area2.80 m²
Wing loading60.0 kg/m²
05
ENVIRONMENT

Reference conditions

Air density1.225 kg/m³
Temperature15.0 °C
Altitude0 m
Headwind12.0 km/h
06
MISSION

Mission 2026-042

Starting SOC100%
Phases5
Mission distance48.1 km
Mission duration29.5 min
Energy consumed15.69 kWh
End SOC / reserve margin86.9% / 66.9%
PhaseDurationDistanceBattery powerEnergyEnd SOC
VTOL1.00 min0.00 km110.4 kW1.84 kWh98.5%
CLIMB1.67 min2.44 km61.9 kW1.72 kWh97.0%
CRUISE23.33 min42.00 km26.2 kW10.18 kWh88.6%
DESCENT2.50 min3.67 km2.6 kW0.11 kWh88.5%
LAND1.00 min0.00 km110.4 kW1.84 kWh86.9%
07
PERFORMANCE AND CONSTRAINTS

Model 0.2 results

StatusCONCEPT FEASIBLE
Estimated range379.5 km
Hover battery power110.4 kW
Cruise battery power26.2 kW
Energy per distance0.326 kWh/km
Input hashfnv1a-a78438c9
ConstraintActualLimitStatus
Hover shaft power91.35 kW440.00 kWPASS
Hover battery power110.40 kW400.00 kWPASS
Required hover thrust5,886.00 N7,600.00 NPASS
Calculated takeoff mass600.00 kg600.00 kgPASS
Required shaft power91.35 kW440.00 kWPASS
Required battery power110.40 kW400.00 kWPASS
Required shaft power50.26 kW440.00 kWPASS
Required battery power61.91 kW400.00 kWPASS
Required lift coefficient1.25 ratio1.50 ratioPASS
Required shaft power19.97 kW440.00 kWPASS
Required battery power26.18 kW400.00 kWPASS
Required lift coefficient0.86 ratio1.50 ratioPASS
Required shaft power0.00 kW440.00 kWPASS
Required battery power2.60 kW400.00 kWPASS
Required lift coefficient1.25 ratio1.50 ratioPASS
Required shaft power91.35 kW440.00 kWPASS
Required battery power110.40 kW400.00 kWPASS
Mission energy15.69 kWh96.00 kWhPASS
08
MODEL TRACEABILITY

Equations and assumptions

Equations used by model 0.2

v02.weightW = m × g
v02.rotor-areaA = N_rotor × π × (d / 2)²
v02.hover-idealP_ideal = T^(3/2) / sqrt(2ρA)
v02.hover-shaftP_shaft = P_ideal / FM
v02.dynamic-pressureq = 0.5ρV²
v02.lift-coefficientCL = W / (qS)
v02.drag-polarCD = CD0 + CL² / (πeAR)
v02.dragD = qSCD
v02.aerodynamic-powerP_aero = D × V
v02.climb-powerP_climb = W × vertical_rate
v02.descent-powerP_required = max(0, P_aero - W × vertical_rate)
v02.electrical-powerP_bus = P_shaft / (η_motor × η_inverter) + P_aux
v02.battery-powerP_battery = P_bus / η_battery
v02.energyE = P_battery × t
v02.socSOC_end = SOC_start - E / E_nameplate × 100
v02.rangeR = d_noncruise + (E_budget - E_noncruise) / (E_cruise / d_cruise)

Assumptions

v02.environment.user-densityAir density is supplied by the aircraft environment and remains constant for the mission.
v02.phase.steady-stateEach mission phase is treated as a steady operating condition; transitions are omitted.
v02.hover.uniform-inflowHover induced power uses uniform actuator-disk momentum theory.
v02.hover.figure-of-meritA user-supplied figure of merit corrects ideal induced power to rotor shaft power.
v02.hover.profile-power-implicitRotor profile and installation losses are represented only through figure of merit.
v02.aero.parabolic-polarWing-borne flight uses CD = CD0 + CL²/(πeAR).
v02.climb.excess-powerClimb adds m × g × vertical rate to drag power.
v02.descent.no-regenerationDescent propulsive power cannot be negative; regenerative energy is not credited.
v02.battery.no-thermal-modelBattery voltage sag, temperature, C-rate derating and thermal behavior are omitted.
v02.range.fixed-profileRange extends the simulated cruise profile after reserving energy for non-cruise phases.
AeroSim Concept Lab · Aquila U-8 · revision 1Schema 1.1A · Model 0.2 · fnv1a-a78438c9