OPTIMAL CANDIDATE
—
Lowest GTOW in selected batch
MINIMUM TAKEOFF MASS (GTOW)
—
Fixed Dry + Battery
BATTERY PACK SIZED
—
Capacity & Nominal Energy
HOVER ELECTRICAL POWER
—
Propulsion + Avionics
HOVER / BURST ESC CURRENT
—
Per motor ESC demand
TOP CLUSTER CANDIDATES
—
Within 4% of optimal GTOW
Takeoff Mass (GTOW) vs Propeller
Lower is better • Color by check verdictHover & Mission Average Power (W)
Electrical draw from batteryAerodynamic Efficiency (g/W) vs Diameter
Thrust loading efficiencyPer-ESC Current: Hover vs Burst (A)
Safety margin for ESC selectionPropeller Batch Trade Table (0 evaluated)
Click any row or the "Deep Dive" button to inspect full subcomponent weights, power, current, and aerodynamic curves.
PASS
CAUTION
FAIL
★ Top Cluster (<4%)
| Propeller ⬍ | D (in) ⬍ | Pitch ⬍ | Type ⬍ | Margin ⬍ | GTOW (kg) ⬍ | Batt (kg) ⬍ | Cap (mAh) ⬍ | Energy (Wh) ⬍ | P hov (W) ⬍ | P mis (W) ⬍ | I hov ESC (A) ⬍ | I pk ESC (A) ⬍ | ESC Size ⬍ | RPM hov% ⬍ | RPM pk% ⬍ | Mach pk ⬍ | g/W ⬍ | Min KV ⬍ | Verdict ⬍ | Action |
|---|
PER3_7x38WSF
PASS
TOTAL VEHICLE TAKEOFF WEIGHT (GTOW)
—
Fixed Dry Mass + Sized Battery Pack
MASS SNOWBALL FACTOR (k)
—
+100g payload → compounding GTOW increase
ELECTRICAL HOVER POWER
—
Propulsion + Continuous Avionics
ESC CURRENT DEMAND (HOVER / BURST)
—
Recommended ESC: —
ENVELOPE RADIAL CLEARANCE
—
Margin to cage inner boundary
⚖️ Subcomponent Mass Accounting
First-Principles Budget| Subcomponent | Mass (kg) | Share (%) |
|---|
⚡ Electrical, Power & Current Breakdown
Powertrain Telemetry| Hover Shaft Power (Total / Per Motor) | — |
| Hover Electrical Propulsion Power | — |
| Continuous Avionics & Payload Draw | — |
| Total Hover Electrical Power | — |
| Mission Average Electrical Power | — |
| Peak Burst Electrical Power | — |
| Steady Hover Current (Total / Per ESC) | — |
| Peak Burst Current (Total / Per ESC) | — |
| Recommended ESC Size (1.5x margin) | — |
| Nominal Battery Capacity & Energy | — |
| Peak Burst C-Rate | — |
| Loaded Bus Voltage under Burst | — |
| Loaded Cell Voltage under Burst | — |
| Approximate Minimum Motor KV | — |
🌪️ Rotor Aerodynamics & Thrust Metrics
APC PER3 Data Interpolation| Operating RPM (Hover / Burst) | — |
| Structural RPM Limit (Ceiling) | — |
| RPM Structural Headroom Utilized | — |
| Tip Speed (Hover / Burst) | — |
| Blade Tip Mach Number (Hover / Burst) | — |
| Hover Power Loading (Efficiency) | — |
| Disk Loading (N/m²) | — |
| Net Hover Thrust per Motor | — |
| Net Burst Thrust per Motor | — |
| Shaft Hover Thrust (before wake/coax losses) | — |
📐 Mechanical Enveloping & Rolling Cage Fit
Host Pipe Fluid Dynamics| Propeller Diameter & Pitch | — |
| Rotor Arrangement | — |
| Total Tip-to-Tip Rotor Footprint | — |
| Inner Cage Clear Envelope | — |
| Radial Tip Clearance to Cage Struts | — |
| Outer Spherical Cage Diameter | — |
| Host Pipe Inner Diameter (ID) | — |
| Annular Return Airflow Gap | — |
| Pipe Cross-Sectional Blockage | — |
| Annular Return Airflow Area | — |
📈 Aerodynamic Characteristic Curves (Static J = 0)
Directly calculated from APC PER3 wind-tunnel / simulation data across operating RPM.
🛡️ Engineering Criteria & Regulatory Verification Checks
Evaluated strictly against first-principles physics, structural ceilings, and IATA Dangerous Goods rules.
| Check Code | Engineering Verification Item | Calculated Value | Design Threshold / Safety Rule | Status |
|---|
🎯 System Sensitivity Matrix (±15% Variations)
Quantifies the impact on Takeoff Mass (GTOW), Battery Mass, and Mission Power when design parameters change.
| Parameter Varied | Condition | GTOW (kg) | Δ GTOW (kg) | Battery (kg) | Mission Power (W) | Capacity (mAh) | Status |
|---|