Digital Research Engine · Research
DIGITAL AERODYNAMIC LABORATORY
Interactive Wind Tunnel — Computational Research Environment
A computational environment for reproducible aerodynamic research, powered by the BLACK WIDOW Digital Research Engine. Explore. Simulate. Compare.
SHOW THE FUTURE. PROVE THE PRESENT.
How It Works
INPUT → COMPUTE → RESULT → EVIDENCE
GEOMETRY
Custom — COMING SOON
Custom geometry computation will become available with the public research gateway.
FLOW CONDITIONS
- Reynolds Number
- 6.0e+6
- Mach Number
- 0.15
STORED POINT
SOLVER
2D viscous aerodynamic computation with boundary-layer modelling.
DIGITAL WIND TUNNEL · STREAMLINES…
CURRENT POINT · α = 8.30°
CL vs α
CD vs α
CASE INFORMATION
- GEOMETRY
- NACA 0012 (TMR altered, DERIVED)
- Reynolds Number
- 6.0e+6
- Mach Number
- 0.15
- Angle of Attack α
- 8.3°
- SOLVER
- A3 / XFOIL 6.99
- Points
- 17 / 16 / 1
CURRENT RESULT
- CL
- 0.9082
- CD
- 0.0082
- CM
- 0.0094
- L/D
- 110.3524
EVIDENCE & PROVENANCE
- experiment ID
- A3_TMR_CL_MATCH_01
- geometry hash
- 634c25ce132e499beb258e0d…
- solver representation hash
- 35ee103cd5cfdeb807bd3a82…
- Campaign Hash
- 9ef5349ccb9c85b1a076a575…
- reproducibility
- PASS
OBJECT B (reference) and the XFOIL solver representation are DISTINCT identities.
CLAIM BOUNDARY
- — deterministic computational result
- — independent NASA reference
- — CL comparison
- — provenance-preserving evidence
- — interpretation of the comparison
- — numerical accuracy
- — experimental agreement
- — physical validation
- — validated NACA0012
- — wind-tunnel equivalence
- — C2 closure
- — G8 readiness
- — C2: DEFERRED / WAIVED
- — G8: NOT READY
Parametric Polar
Geometry-aware Inviscid
Viscous 2D
Deterministic Experiments
Provenance
Evidence Packages
Reference Comparison
VLM / Lifting Line
CFD
Physical Validation
The public interface is prepared for live research execution. Current public mode uses reproducible stored (precomputed) evidence.
Deterministic computational results only. No physical validation is performed. This is a computational research environment for reproducible aerodynamic experiments.
Claim Boundary
Supported
- — deterministic computational result
- — independent NASA reference
- — CL comparison
- — provenance-preserving evidence
Conditional
- — interpretation of the comparison
Not Established
- — numerical accuracy
- — experimental agreement
- — physical validation
- — validated NACA0012
- — wind-tunnel equivalence
- — C2 closure
- — G8 readiness