Roshan Aerospace IndustriesContact ↗

RAI-AIR-001 / Conceptual design completed

UAV Concept V1

RAI / Evidence-led development

A documented fixed-wing V-tail pusher concept. CAD complete; airworthiness, structural validation, and flight testing remain future work.

GalleryTechnical recordMathematics3D modelDocuments

02 / Engineering record

What was actually done

UAV Concept V1 established a coherent aircraft configuration, principal geometry, internal packaging, and engineering-documentation workflow. The concept uses a V-tail and rear pusher propeller. It is a portfolio CAD and analysis project—not a production aircraft and not yet flight-ready.

Evidence available

  • Completed external CAD geometry
  • Engineering dimensions and orthographic views
  • Configuration and packaging study
  • 22-page project report referenced in the project record
  • Version-controlled repository planned for public evidence

Recorded dimensions & specifications

Wingspan1,900 mm
Fuselage length1,280 mm
Wing chord190 mm
Wing area0.361 m²
Aspect ratio≈ 10.0
ConfigurationV-tail / pusher

03 / Mathematics

Calculations, not decoration

Wing areaS = b × c = 1.90 × 0.19 = 0.361 m²

Rectangular reference-planform estimate used for the concept.

Aspect ratioAR = b² / S = 1.90² / 0.361 ≈ 10.0

Indicates a relatively slender wing, subject to later aerodynamic validation.

Lift relationL = ½ρV²SCL

Framework for future lift and speed calculations; no validated CL dataset is claimed.

04 / Interactive engineering model

3D release pending

No verified STL or browser-ready glTF file is currently available in the project archive. A fake model would damage credibility. This viewer area is intentionally locked until the real export is checked, versioned, and approved for public release.

RAI / MODEL GATESTL / GLB
NOT RELEASEDModel ownership and public-release review required

05 / Documentation

Reports & release record

Technical reportPublic file not yet availableRelease pending

Declared limitations

  • Airfoil selection not finalized
  • No structural or aeroelastic analysis
  • Weight, CG, and stability model incomplete
  • No CFD or wind-tunnel validation
  • No prototype or flight-test evidence
  • Public report file and STL export not yet released