Research Overview
Research
Overview of research programs, methods, and knowledge.
DIGITAL RESEARCH LABORATORY
A unified computational environment for reproducible research across the nine canonical BLACK WIDOW technologies.
OPEN LABORATORY
DIGITAL AERODYNAMIC LABORATORY
Explore reproducible computational aerodynamic experiments, their provenance, and evidence.
OPEN LABORATORY · VIEW EVIDENCE
PUBLIC RESEARCH API
Read-only machine-readable research evidence.
Research Programs
BLACK WIDOW conducts research across multiple technology areas, from mechanical systems to software orchestration.
Program 08 — Swarm Intelligence
Research Concept · Simulation Only · In Development
Multi-agent coordination research. No flight validation.
Methods
Simulation, Monte Carlo analysis, digital twin validation, physical experimentation.
Knowledge
Research Knowledge Base, validation dossiers, evidence matrices.
Technology Status
Mission OS
Research Operating System
BW-C45
Sub-Drone Deployment System
EPM
Electro-Permanent Magnet Docking & Release
GPS-Denied
Navigation in GPS-Denied Environments
ALBATROSS
Aerial Launch & Recovery System
OWL
Leading/Trailing Edge Serration Research
FlyScout
Hybrid Air/Ground Reconnaissance Micro-Drone
Swarm Intelligence
Multi-Agent Coordination Research
Digital Twin
High-Fidelity Simulation Environment
Research Milestone
21 September 2026
A2 — Geometry-Aware 2D Inviscid Aerodynamic Model
Qualified with conditionsBLACK WIDOW has completed A2 of its Digital Aerodynamic Engine — a geometry-aware 2-D inviscid aerodynamic model based on a Hess–Smith source/vortex panel method. The model takes airfoil geometry and flow conditions and computes the surface velocity distribution V_t(s), the pressure-coefficient distribution Cp(s), circulation Γ, the lift coefficient CL, the pitching-moment coefficient CM, the zero-lift angle α_L0 and the stagnation-point location.
Independent verification
- 116 / 116 overall tests PASS
- 34 / 34 A2 tests PASS
- V1–V12: 12 / 12 PASS
- influence coefficients independently checked: ≤ 2×10⁻¹³
- Kutta residual: ~10⁻¹³
- deterministic execution
- reproducible evidence
- panel-count convergence verified
Computational chain
- 01Airfoil geometry
- 02Panel discretization
- 03Hess–Smith source/vortex solution
- 04V_t(s)
- 05Cp(s)
- 06CL / CM / Γ
- 07Reproducible evidence
At this level the aerodynamic coefficients are computed from the airfoil geometry within a defined inviscid model, rather than being supplied as a fixed parametric polar.
Scientific scope and limitations
The current model describes 2-D incompressible inviscid flow. It is not a physically validated model and does not use measured aerodynamic parameters. At this stage the model does not describe:
- viscous drag
- Reynolds-number dependence
- laminar/turbulent transition
- flow separation
- realistic stall
- turbulence
- 3-D / finite-wing effects
- compressibility
- CFD / RANS
- experimental calibration
A3 — viscous aerodynamic modelling — NOT STARTED