scholarly journals Experimental Study on Slat Noise from 30P30N Three-Element High-Lift Airfoil at JAXA Hard-Wall Lowspeed Wind Tunnel

2014 ◽  
Author(s):  
Mitsuhiro Murayama ◽  
Kazuyuki Nakakita ◽  
Kazuomi Yamamoto ◽  
Hiroki Ura ◽  
Yasushi Ito ◽  
...  
Keyword(s):  
Experimental Study ◽  
Wind Tunnel ◽  
Hard Wall ◽  
High Lift ◽  
Slat Noise

Experimental Study of Slat Noise from 30P30N Three-Element High-Lift Airfoil in JAXA Kevlar-Wall Low-Speed Wind Tunnel

2018 ◽  
Author(s):  
Mitsuhiro Murayama ◽  
Yuzuru Yokokawa ◽  
Hiroki Ura ◽  
Kazuyuki Nakakita ◽  
Kazuomi Yamamoto ◽  
...  
Keyword(s):  
Experimental Study ◽  
Wind Tunnel ◽  
High Lift ◽  
Low Speed ◽  
Slat Noise ◽  
Low Speed Wind Tunnel

Validation of computed high-lift flows with significant wind-tunnel effects

AIAA Journal ◽  
2001 ◽  
Vol 39 ◽  
pp. 1884-1892
Author(s):  
Stuart E. Rogers ◽  
Karlin Roth ◽  
Steven M. Nash
Keyword(s):  
Wind Tunnel ◽  
High Lift ◽  
Tunnel Effects

Wind Tunnel Experiment of Microjet-based Flow Control on a Multi-Element High-Lift Airfoil

2022 ◽  
Author(s):  
Case P. Van Dam ◽  
Sai B. Mothukuri ◽  
Seyedeh Sheida Hosseini ◽  
Edward White ◽  
Lisa Brown ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Flow Control ◽  
Wind Tunnel Experiment ◽  
High Lift

Aeroacoustic analysis of slat tones

2021 ◽  
Vol 263 (1) ◽  
pp. 5650-5663
Author(s):  
Hasan Kamliya Jawahar ◽  
Syamir Alihan Showkat Ali ◽  
Mahdi Azarpeyvand
Keyword(s):  
Wavelet Transform ◽  
Surface Pressure ◽  
Wavelet Coefficient ◽  
Pressure Fluctuations ◽  
Low Frequency ◽  
Stream Velocity ◽  
High Lift ◽  
Unsteady Surface Pressure ◽  
Slat Noise ◽  
Generation Mechanisms

Experimental measurements were carried out to assess the aeroacoustic characteristics of a 30P30N high-lift device, with particular attention to slat tonal noise. Three different types of slat modifications, namely slat cove filler, serrated slat cusp, and slat finlets have been experimentally examined. The results are presented for an angle of attack of α = 18 at a free-stream velocity of U = 30 m/s, which corresponds to a chord-based Reynolds number of Re = 7 x 10. The unsteady surface pressure near the slat region and far-field noise were made simultaneously to gain a deeper understanding of the slat noise generation mechanisms. The nature of the low-frequency broadband hump and the slat tones were investigated using higher-order statistical approaches for the baseline 30P30N and modified slat configurations. Continuous wavelet transform of the unsteady surface pressure fluctuations along with secondary wavelet transform of the broadband hump and tones were carried out to analyze the intermittent events induced by the tone generating resonant mechanisms. Stochastic analysis of the wavelet coefficient modulus of the surface pressure fluctuations was also carried out to demonstrate the inherent differences of different tonal frequencies. An understanding into the nature of the noise generated from the slat will help design the new generation of quite high-lift devices.

scholarly journals Experimental Study on Cooling effects of River using Wind Tunnel

1994 ◽  
Vol 38 ◽  
pp. 393-400
Author(s):  
Shigeki KOBATAKE ◽  
Yoshihiko SHIMIZU ◽  
Ritsuko AOKI ◽  
Fumika HAYASAKA ◽  
You ANDOU
Keyword(s):  
Experimental Study ◽  
Wind Tunnel ◽  
Cooling Effects

scholarly journals Experimental Study of Dynamic Wind Tunnel and Flight Simulator Coupling

2014 ◽  
Vol 62 (4) ◽  
pp. 117-122
Author(s):  
Kohei MIYAZONO ◽  
Kenta YOSHIDA ◽  
Yasuto SUNADA ◽  
Taro IMAMURA
Keyword(s):  
Experimental Study ◽  
Wind Tunnel ◽  
Flight Simulator ◽  
Simulator Coupling

Characterisation of a highly staggered spanwise cambered biplane

2015 ◽  
Vol 119 (1212) ◽  
pp. 203-228
Author(s):  
L.W. Traub ◽  
R. Waghela ◽  
K.A. Bordignon
Keyword(s):  
Numerical Simulation ◽  
Wind Tunnel ◽  
Dihedral Angles ◽  
Wind Tunnel Testing ◽  
High Lift ◽  
Front Wing ◽  
Geometric Variation ◽  
Tunnel Testing

AbstractAn investigation is presented to elucidate the performance of a staggered, spanwise cambered biplane. The spanwise camber yielded wings forming a ‘∧’ or ‘∨’ when viewed streamwise. The configuration is examined in terms of its aerodynamic and stability characteristics. The feasibility of negating the requirement for a conventional empennage is explored. Geometric variation encompassed front and back wing anhedral/dihedral angles yielding 49 combinations. Evaluation of the geometry was accomplished using both wind tunnel testing and numerical simulation. The results indicated that front wing dihedral in conjunction with aft wing anhedral was most beneficial, such that the benefit of wake spacing was maximised. Aerodynamic benefit was indicated compared to a conventional empennage geometry. The greatest disparity in behaviour of the fore and aft wing anhedral/dihedral distribution was in the high lift regime, where the nature of the stall varied. Simulations to establish the viability of the geometry in terms of controllability were also conducted and indicated that the configuration is viable.

Sign in / Sign up

Export Citation Format

Share Document