scholarly journals Experimental Investigation on the Effect of Multi-Winglets

2011 ◽  
pp. 43-46
Author(s):  
Srikanth G, ◽  
Surendra Bogadi
Keyword(s):  
Experimental Study ◽  
Experimental Investigation ◽  
Wind Tunnel ◽  
Flow Visualization ◽  
Flow Speed ◽  
Aircraft Wing ◽  
Induced Drag ◽  
Subsonic Wind Tunnel ◽  
Wingtip Vortex ◽  
Naca 0015

An extensive experimental study is conducted to examine the potentiality of Multi-Winglets (similar to bird tip feathers) for the reduction of Induced Drag, improved CL without increase in span of aircraft wing. The model composed of a rectangular wing built from NACA 0015 airfoil constituted of three winglets, which are small wings without sweep & twist. The test conducted in subsonic wind tunnel at flow speed 20m/s and placing the wing at angle of attack ranging from -5 to +15 deg. And also the wing with no winglet (bare wing) and with single winglet also tested in the same condition as in the case of three winglets (multi-winglet). Wind tunnel balances provided lift measurements and tuft flow visualization obtained wingtip vortex information. The results show that multi-winglet system reduced induced drag by 27.9% and improved CL by 26.5% compare to bare wing.

An Experimental Study of the Heat Balance in a Subsonic Wind Tunnel

2022 ◽  
Author(s):  
Evan Pruitt ◽  
Chandara Heng ◽  
John King ◽  
Amaury Reed ◽  
Xiaofeng Liu
Keyword(s):  
Experimental Study ◽  
Wind Tunnel ◽  
Heat Balance ◽  
Subsonic Wind Tunnel ◽  
The Heat Balance

scholarly journals Design and analysis of smoke flow visualization apparatus for wind tunnel

2021 ◽  
Vol 1206 (1) ◽  
pp. 012014
Author(s):  
D Raval ◽  
S V Jain ◽  
A M Acharii ◽  
K Ghosh
Keyword(s):  
Wind Tunnel ◽  
Flow Visualization ◽  
Operating Conditions ◽  
Design Flow ◽  
Column Height ◽  
Stream Velocity ◽  
Variable Frequency Drive ◽  
Power Inputs ◽  
Fan Speed ◽  
Naca 0015

Abstract In the present study, the design and analysis of smoke generator are done for the low-speed wind tunnel. The wind tunnel fan is fitted with the Variable Frequency Drive to produce the wind speed in the range of 3 to 32 m/s with fan speed of 150 to 1500 rpm. The design of smoke generator was done according to Preston Sweeting mist generator principle corresponding to the free stream velocity of 3 m/s. A controlled smoke generator consisting of kerosene reservoir, controlled heater, blower, liquid column height adjustment mechanism, valves etc. was designed and fabricated. The smoke generator produced the smoke at the rate of 154 cm3/s which was close to the design flow rate of 149 cm3/s. To supply the required quantity of smoke in the wind tunnel, the smoke rake of NACA 0010 profile was developed and installed in the rapid contraction section of the wind tunnel to achieve the streamlined flow. The parametric studies were done on the smoke generator at different power inputs and its effects were studied on smoke temperature, smoke discharge and boiling time of the kerosene. The flow visualization was carried out on NACA 0015 airfoil model and the images were captured to examine the flow physics around them under different operating conditions.

Experimental study on correlation between turbulence and sound in a subsonic wind tunnel

2010 ◽  
Vol 26 (4) ◽  
pp. 531-539 ◽  
Author(s):  
M. D. Manshadi ◽  
K. Ghorbanian ◽  
M. R. Soltani
Keyword(s):  
Experimental Study ◽  
Wind Tunnel ◽  
Subsonic Wind Tunnel

scholarly journals PENELITIAN DAN RANCANGAN OPTIMAL TURBIN PENGGERAK TEROWONGAN ANGIN SUBSONIK SIRKUIT TERBUKA LAPAN

2010 ◽  
Vol 2 (2) ◽  
Author(s):  
Sulistyo Atmadi
Keyword(s):  
Wind Tunnel ◽  
Power System ◽  
Flow Condition ◽  
Flow Speed ◽  
Optimal Result ◽  
Free Vortex ◽  
Optimization Result ◽  
Subsonic Wind Tunnel ◽  
Speed Up

In an effort to improve flow condition and flow speed up to 50 m per s inside LAPAN Subsonic Wind Tunnel, an existing power system and turbine has to be redesigned. Specifications for these requirments have been determined and calculated for the required power and aerofoil type and their dimensions. A method based free vortex design was used to get optimal result. The optimization result produced a turbine with 3 m diameter, with 10 blades, 1.5 m hub diameter. A D RAF PROPELLER aerofoil type was used to produce 230 HP power and 1824 Nm torque, with an efficience 89 percent. This result was considered both technically and economically.

A parametric study of airframe effects on the noise emission from installed contra-rotating open rotors

2018 ◽  
Vol 17 (6-8) ◽  
pp. 624-654 ◽  
Author(s):  
J Kennedy ◽  
P Eret ◽  
GJ Bennett
Keyword(s):  
Experimental Investigation ◽  
Wind Tunnel ◽  
Parametric Study ◽  
Emission Angle ◽  
Flow Speed ◽  
Scale Model ◽  
Far Field ◽  
Noise Emission ◽  
Rotor Noise ◽  
Open Rotor

This work reports on the results of the Clean Sky WENEMOR project which has conducted an extensive experimental investigation of installed contra-rotating open rotors on a scale model of an advanced regional aircraft configuration. The tests were conducted in the Pininfarina Wind Tunnel, Italy and the data used for this analysis were taken from a linear far-field array of microphones. The contra-rotating open rotors were operated in pusher and tractor modes with approach and takeoff settings for revolutions per minute and thrust. Realistic modern blade profiles were supplied and utilized through the Clean Sky Green Regional Aircraft program. A range of airframe geometries was tested which included interchangeable tails, engine pylon elongation, engine pylon rotation, and variable wing to engine distance. Changes in the contra-rotating open rotor noise emission to the far field as a function of flow speed, angle of attack, and airframe geometry were clearly identified. The influence of airframe geometry on contra-rotating open rotor tonal content, directivity, and broadband levels is reported for emission angles from [Formula: see text] to [Formula: see text]. Both significant noise increases and decreases with respect to the baseline airframe configurations were detected in both the tonal and broadband levels as a function of emission angle (ranging from 10 to 25 dB at the blade passing frequency tones). While the changes to the tonal level were generally greater than those of the broadband level, the broadband levels are shown to be significant when considering the influence of airframe geometries on contra-rotating open rotor noise emission.

Effects of Turbulence on the Breakup of Round Liquid Jets in Gaseous Crossflow

2005 ◽  
Author(s):  
R. Sankarakrishnan ◽  
K. A. Sallam ◽  
F. W. Chambers
Keyword(s):  
Experimental Investigation ◽  
Wind Tunnel ◽  
Test Section ◽  
Drop Size ◽  
Liquid Surface ◽  
Liquid Jets ◽  
Liquid Jet ◽  
Surface Conditions ◽  
Subsonic Wind Tunnel ◽  
Primary Breakup

An experimental investigation of the effects of turbulence on primary breakup of round liquid jets subjected to gaseous crossflow is described. The paper investigates the effects of partial degrees of turbulence development in the liquid. Measurements of the properties of primary breakup were obtained using double-pulsed shadowgraphy in a subsonic wind tunnel having a test section of 0.3 m × 0.3 m × 0.6 m. Measurements included primary breakup regimes, conditions required for the onset of breakup, ligament properties along the liquid surface, drop size and velocity distributions after breakup along the liquid surface, conditions required for breakup of the liquid jet as a whole, and liquid jet trajectories.

Sign in / Sign up

Export Citation Format

Share Document