Aquila U-8WHAT-IF ANALYSIS / MODEL 0.2

Baseline vs modified

Explore parameter changes against the saved Mission 2026-042 baseline without modifying its source records.

Open simulator
SCENARIO STATUS

Baseline reproduced

CONCEPT FEASIBLE
Estimated range
BASELINE379.5 km
MODIFIED379.5 km
0.0 km
Mission energy
BASELINE15.69 kWh
MODIFIED15.69 kWh
0.00 kWh
End SOC
BASELINE86.9 %
MODIFIED86.9 %
0.0 %
Mission duration
BASELINE29.5 min
MODIFIED29.5 min
0.0 min
Hover power
BASELINE110.4 kW
MODIFIED110.4 kW
0.0 kW
Cruise power
BASELINE26.2 kW
MODIFIED26.2 kW
0.0 kW
Energy / distance
BASELINE0.326 kWh/km
MODIFIED0.326 kWh/km
0.000 kWh/km
Thrust / weight
BASELINE1.29 ratio
MODIFIED1.29 ratio
0.00 ratio
INDEXED COMPARISON

Baseline = 100

Preparing comparison…

Each metric is indexed independently so unlike units are not plotted on a shared physical scale.

ONE-CHANGE-AT-A-TIME

Measured input impacts

Modify an input to measure its isolated effect.
VALIDATED MODEL CHECKS

Modified-case constraints

Hover shaft power91.3 / 440.0 kWPASS
Hover battery power110.4 / 400.0 kWPASS
Required hover thrust5,886.0 / 7,600.0 NPASS
Calculated takeoff mass600.0 / 600.0 kgPASS
Required shaft power91.3 / 440.0 kWPASS
Required battery power110.4 / 400.0 kWPASS
Required lift coefficient1.2 / 1.5 ratioPASS
Mission energy15.7 / 96.0 kWhPASS
BASELINE INPUT HASHfnv1a-a78438c9
MODIFIED INPUT HASHfnv1a-a78438c9
V2F / DETERMINISTIC FACTS

Engineering explanations

These statements are rendered from structured model facts. Traceability categories describe the evidence available, not statistical certainty or engineering validation.

Model 0.2 → 0.2 · fnv1a-a78438c9 → fnv1a-a78438c9

All changed engineering inputs are context for the comparison. The facts do not isolate their individual effects. Phase outputs are matched by phase ID; missing phases stay explicit.

No changed engineering facts in the compared coverage. Identity and descriptive text changes are excluded.

Complete structured comparison JSON (explanations-1)
{
  "version": "explanations-1",
  "status": "ready",
  "facts": [],
  "issues": [],
  "provenance": {
    "baselineModelVersion": "0.2",
    "modifiedModelVersion": "0.2",
    "baselineInputHash": "fnv1a-a78438c9",
    "modifiedInputHash": "fnv1a-a78438c9",
    "scope": "whole-simulation",
    "equationIds": [
      "v02.aerodynamic-power",
      "v02.battery-power",
      "v02.climb-power",
      "v02.descent-power",
      "v02.drag",
      "v02.drag-polar",
      "v02.dynamic-pressure",
      "v02.electrical-power",
      "v02.energy",
      "v02.hover-ideal",
      "v02.hover-shaft",
      "v02.lift-coefficient",
      "v02.range",
      "v02.rotor-area",
      "v02.soc",
      "v02.weight",
      "v2f.difference",
      "v2f.upper-constraint"
    ],
    "assumptionIds": [
      "v02.aero.parabolic-polar",
      "v02.battery.no-thermal-model",
      "v02.climb.excess-power",
      "v02.descent.no-regeneration",
      "v02.environment.user-density",
      "v02.hover.figure-of-merit",
      "v02.hover.profile-power-implicit",
      "v02.hover.uniform-inflow",
      "v02.phase.steady-state",
      "v02.range.fixed-profile",
      "v2f.comparison-only"
    ]
  }
}