2D scaled model of the TURBOPROP wing
Journal Title: INCAS BULLETIN - Year 2011, Vol 3, Issue 4
Abstract
The 2D Turbo Prop wing is part of the European Clean Sky JTI GRA Low Noise programme. For this, the model is equipped with interchangeable T.E. noise reducing systems. The scope of the tests in the INCAS Subsonic wind tunnel is to investigate and compare the aerodynamic and aero acoustic performances of a series of different T.E. High Lift Devices noise reducing systems of the “Turbo Prop wing configuration”. For this, the distribution of the pressure at the surface of the model should be determined. The measurement of the pressure is classically made through orifices of small size connected to a common transducer via a tubing system and a scanning device. The aerodynamic forces and moments are obtained by integration of the pressure and shear stress distributions. The wing span of the model is equal to the width of the test section. Due to the large wing span B = 2500 mm and the testing speed V = 90 m/s, the aerodynamic forces and moments occurring on the model exceed more than two times the measuring capacity of the TEM external balance of the INCAS Subsonic wind tunnel. This imposes attaching the model to supports situated outside the wind tunnel.
Authors and Affiliations
Adrian DOBRE
Keywords
Related Articles
- EP ID EP103066
- DOI 10.13111/2066-8201.2011.3.4.12
- Views 104
- Downloads 0
Scaling of Airborne Ad-hoc Network Metrics with Link Range and Satellite Connectivity
In this contribution, large-scale commercial aeronautical ad-hoc networks are evaluated. The investigation is based on a simulation environment with input from 2016 flight schedule and aircraft performance databases for...
Subsonic Jet Pump Comparative Analysis
The paper presents the numerical and experimental studies carried out to optimize, from an aerodynamic point of view, a subsonic jet pump used on aircraft. The optimization of the subsonic jet pump will be done from the...
FAI First Article Inspection in production activity
This article aims to present the First Article Inspection of production activity of the QTS-2 Quick Thermal Shock equipment. First Article Inspection FAI is analyzed using the definition guidance from IAQG - Internationa...
SIMULAND - A CODE TO ANALYZE DYNAMIC EFFECTS DURING LANDING
The landing gear of an aircraft is part of the aircraft structure. It is the most critical part of the flight mission and also the component that will likely cause the most problems in the aircraft design. The landing ge...
Reducing Fuel Consumption in Bucharest Terminal Area for Flights Using a Standard Instrument Departure
Reconfiguration of the standard instrument departure and standard arrival routes at certain airports can bring significant reductions in fuel consumption and level of noise. This can be done either by implementing modern...