scholarly journals Experimental Investigation and Theoretical Prediction of Flutter Behaviour of a Plane Cascade in Low-Speed Flow

1996 ◽  
Author(s):  
H. Hennings ◽  
W. Send
Keyword(s):  
Cross Section ◽  
Transonic Flow ◽  
Close Relation ◽  
Test Facility ◽  
Aerodynamic Forces ◽  
Low Speed ◽  
Air Stream ◽  
Speed Flow ◽  
Sensitive Dependence ◽  
Flutter Boundary

The Institute of Aeroelasticity operates a test facility which enables aeroelastic investigations of plane cascades in low-speed flow. The test stand serves as a pilot facility to develop tools for analogous investigations in transonic flow. Eleven blades are elastically suspended in a windtunnel with a 1 × 0.2 m2 cross section. This paper describes the experimental method of determining the flutter boundary by extrapolation of the results measured in subcritical flow. A 2D theoretical model of the 11 blades including the windtunnel walls permits the computation of unsteady pressures, forces and moments in close relation to the experiment. The prediction of flutter is compared with experimental results. In the present investigation, the motion of the blades is constrained to pitch around mid-chord. The vibrating blades are mechanically uncoupled. Any interaction between the blades is effected by the air stream, leading to a sensitive dependence on the aerodynamic forces.

Experimental Investigation and Theoretical Predication of Flutter Behavior of a Plane Cascade in Low Speed Flow

1998 ◽  
Vol 120 (4) ◽  
pp. 766-774 ◽  
Author(s):  
H. Hennings ◽  
W. Send
Keyword(s):  
Cross Section ◽  
Transonic Flow ◽  
Close Relation ◽  
Test Facility ◽  
Aerodynamic Forces ◽  
Low Speed ◽  
Air Stream ◽  
Speed Flow ◽  
Sensitive Dependence ◽  
Flutter Boundary

The Institute of Aeroelasticity operates a test facility which enables aeroelastic investigations of plane cascades in low-speed flow. The test stand serves as a pilot facility to develop tools for analogous investigations in transonic flow. Eleven blades are elastically suspended in a windtunnel with a 1 × 0.2 m2 cross section. This paper describes the experimental method of determining the flutter boundary by extrapolation of the results measured in subcritical flow. A two-dimensional theoretical model of the 11 blades, including the windtunnel walls, permits the computation of unsteady pressures, forces, and moments in close relation to the experiment. The prediction of flutter is compared with experimental results. In the present investigation, the motion of the blades is constrained to pitch around mid-chord. The vibrating blades are mechanically uncoupled. Any interaction between the blades is effected by the air stream, leading to a sensitive dependence on the aerodynamic forces.

scholarly journals Development of $${\rm N}_2{\rm O}$$ N 2 O -MTV for low-speed flow and in-situ deployment to an integral effect test facility

2017 ◽  
Vol 59 (1) ◽  
Author(s):  
Matthieu A. André ◽  
Ross A. Burns ◽  
Paul M. Danehy ◽  
Seth R. Cadell ◽  
Brian G. Woods ◽  
...  
Keyword(s):  
Test Facility ◽  
Low Speed ◽  
Speed Flow ◽  
Integral Effect ◽  
Effect Test

Hot-wire probes in low speed flow

1979 ◽  
Vol 18 ◽  
pp. 271-323 ◽  
Author(s):  
J.-D. Vagt
Keyword(s):  
Hot Wire ◽  
Low Speed ◽  
Speed Flow

Turbulent Surface Pressure Field in Low Speed Flow

2014 ◽  
pp. 91-100
Author(s):  
Stéphane Caro ◽  
Vincent Cotoni ◽  
Phil Shorter ◽  
Fred Mendonça
Keyword(s):  
Surface Pressure ◽  
Pressure Field ◽  
Low Speed ◽  
Speed Flow

scholarly journals Software Sensor for Airflow Modulation and Noise Detection by Cyclostationary Tools

Sensors ◽  
2020 ◽  
Vol 20 (8) ◽  
pp. 2414
Author(s):  
Mohamad Alkoussa Dit Albacha ◽  
Laurent Rambault ◽  
Anas Sakout ◽  
Kamel Abed Meraim ◽  
Erik Etien ◽  
...  
Keyword(s):  
Flow Rate ◽  
Physical Phenomenon ◽  
Experimental Setup ◽  
Noise Detection ◽  
Air Flow Rate ◽  
Audio Signals ◽  
Software Sensor ◽  
Low Speed ◽  
Speed Flow ◽  
Noise Disturbances

The paper presents tools to model low speed airflow coming from a turbulent machine. This low speed flow have instabilities who generate noise disturbances in the environment. The aim of the study proposed in this paper, is the using of cyclostationary tools with audio signals to model this airflow and detect the noisy frequencies to eliminate this noise. This paper also deals with the extraction in real time of the frequency corresponding to the noise nuisance. This extraction makes it possible to build a software sensor. This software sensor can be used to estimate the air flow rate and also to control a future actuator which will reduce the intensity of the noise nuisance. This paper focuses on the characteristic of the sound signal (property of cyclostationarity) and on the development of a software sensor. The results are established using an experimental setup representative of the physical phenomenon to be characterised.

scholarly journals Numerical Simulation for Engine/Airframe Interaction Effects of the BWB300 on Aerodynamic Performances

2019 ◽  
Vol 2019 ◽  
pp. 1-15 ◽  
Author(s):  
Gang Yu ◽  
Dong Li ◽  
Yue Shu ◽  
Zeyu Zhang
Keyword(s):  
Numerical Simulation ◽  
High Speed ◽  
Separated Flow ◽  
Simulation Method ◽  
Interaction Effects ◽  
Surface Flow ◽  
Concept Design ◽  
Aerodynamic Forces ◽  
Low Speed ◽  
Aerodynamic Performances

The engine/airframe interaction effects of the BWB300 on aerodynamic performances were analyzed by using the numerical simulation method. The BWB300 is a 300-seat Blended Wing Body airplane designed by the Airplane Concept Design Institute of Northwestern Polytechnical University. The engine model used for simulation was simplified as a powered nacelle. The results indicated the following: at high speed, although the engine/airframe interaction effects on the aerodynamic forces were not significant, the airframe’s upper surface flow was greatly changed; at low speed, the airframe’s aerodynamic forces (of the airplane with/without the engine) were greatly different, especially at high attack angles, i.e., the effect of the engine suction caused the engine configuration aerodynamic forces of the airframe to be bigger than those without the engine; and the engine’s installation resulting in the different development of flow separation at the airframe’s upper surface caused greater obvious differences between the 2 configurations at high angles and low speed. Moreover, at low-speed high attack angles, the separated flow from the blended area caused serious distortion at the fan inlet of the engine.

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