Micro-air vehicle Aerodynamics Research tunnel (MART) is a special purpose low speed wind tunnel facility for aero-propulsion characterization of various UAV configurations
Measurement of aerodynamic forces and moments for various fixed-wing UAV configurations
Static and dynamic characterization of various propellers for UAV applications
Surface pressure measurements over wings
Flow field (velocity) measurements in wake of test models
Smoke flow and surface oil flow visualization studies
Geometric Specifications and Flow Characteristics | |
Type | Open Circuit, Suction |
Contraction Ratio | 9:1 |
Test section | Closed TS: 0.8 m (width) x 1.2 m (height) x 2.5 m (length) Open Jet: 0.8 m (width) x 1.2 m (height) x 1 m (length) |
Velocity Range | Closed TS : 1 to 40 m/s Open Jet: 1 to 20 m/s |
Mean flow velocity variation | ±0.1 % |
Turbulence Intensity | Up to 10 m/s : < 0.1 % 10 m/s to 45 m/s : < 0.15 % |
Some of the key features of this facility include the open/ closed test section with BETZ pressure chamber, low freestream turbulence levels, active gust generation mechanism and retractable screens. MART would address all the aerodynamics, propulsion and aero elastic issues using advanced investigating tools like low load force balances, low magnitude pressure scanners and, optical flow diagnostics system. The open jet type test section would provide the advantage of wall interference free testing related to flapping and rotary wings. The longitudinal sinusoidal variation in the freestream velocity can be generated with help of active gust generation mechanism which would help in studying stability and aero elasticity issues in UAV under gusty environment.
