Flight Simulation Technologies Conference and Exhibit · 1990 · 48 citations · 4 references
EngineeringAerospace EngineeringMechanical EngineeringAerodynamicsAircraft DesignFluid DynamicsAerodynamic TestingAircraft StabilityExperimental AerodynamicsFlow StabilityHydrodynamic StabilityWing AerodynamicsAircraft Aerodynamics TestingAircraft Stability AnalysisBoundary Layer InstabilityBoundary Layer StabilityCrossflow InstabilityFlightFlow Stability AnalysisMach Number
The glove was designed to capture Tollmien‑Schlichting, crossflow, and attachment‑line transition instabilities in the boundary layer. Flight tests were conducted on the right‑hand wing of the DLR VFW 614/ATTAS, measuring pressure distributions and using them in stability analyses to study the glove’s effect on boundary‑layer instabilities. Infrared imaging revealed the full transition line over Mach 0.35–0.7, stability calculations predicted large‑Reynolds‑number behavior, and disturbance studies highlighted the roles of engine noise and geometric steps on transition location.
As part of a national laminar low research program, flight tests with a glove on the right-hand wing of the DLR research aircraft VFW 614/ATTAS were carried out. The glove was especially designed to obtain three types of boundary layer instability: Tollmien-Schlichting instability (TSI), crossflow instability (CFI) and attachment line transition (ALT). In all tests, covering the Mach number range from 0.35 to 0.7, the complete transition line has been made visible by infrared image technique. Pressure distributions were measured and and used in stability analyses. Thus prediction by stability calculations at large Reynolds numbers has been obtained. Initial disturbance investigations provided information on the influence of engine noise and geometric steps on transition location.
4