Mathematical Model for the Starting Process of a Transonic Ludwieg Tube Wind Tunnel

1977 ◽  
Vol 14 (6) ◽  
pp. 519-520 ◽  
Author(s):  
F. L. Shope
Keyword(s):  
Mathematical Model ◽  
Wind Tunnel ◽  
Ludwieg Tube ◽  
Starting Process

Optimization Calculation of Javelin Throwing Results

2014 ◽  
Vol 716-717 ◽  
pp. 764-766
Author(s):  
Min Jiang ◽  
Ji He Zhou
Keyword(s):  
Mathematical Model ◽  
Wind Tunnel ◽  
Initial Velocity ◽  
Angle Of Attack ◽  
Wind Tunnel Experiment ◽  
Aerodynamic Efficiency ◽  
Optimization Calculation ◽  
Computer Optimization ◽  
Necessary And Sufficient

On the basis of javelin wind tunnel experiment, we established mathematical model of javelin flight to conduct a computer optimization and got the conclusions. When the initial velocity is in the range of 25m/s-30m/s, the best throwing condition is: the throwing angle is 40°, the angle of attack is 11°. The javelin throwing condition is not zero angle of attack was necessary and sufficient for obtained aerodynamic efficiency.

Flight Characteristics of Flapping Wing Miniature Air Vehicles With “Figure-8” Spherical Motion

2009 ◽  
Author(s):  
Mohamed B. Trabia ◽  
Woosoon Yim ◽  
Zohaib Rehmat ◽  
Jesse Roll
Keyword(s):  
Mathematical Model ◽  
Wind Tunnel ◽  
Experimental Testing ◽  
Flapping Wing ◽  
Dynamic Stall ◽  
Wind Tunnel Testing ◽  
Servo Motor ◽  
Aerodynamic Forces ◽  
Flapping Motion ◽  
Spherical Motion

Hummingbirds and some insects exhibit “Figure-8” flapping motion that allows them to go through a variety of maneuvers including hovering. Understanding the flight characteristics of Figure-8 flapping motion can potentially yield the foundation of flapping wing UAVs that can experience similar maneuverability. In this paper, a mathematical model of the dynamic and aerodynamic forces associated with Figure-8 motion generated by a spherical four bar mechanism is developed. For validation, a FWMAV prototype with the wing attached to a coupler point and driven by a DC servo motor is created for experimental testing. Wind tunnel testing is conducted to determine the coefficients of flight and the effects of dynamic stall. The wing is driven at speeds up to 12.25 Hz with results compared to that of the model. The results indicate good correlation between mathematical model and experimental prototype.

Film cooling experimental technique using a Ludwieg tube wind tunnel

1993 ◽  
Vol 6 (2) ◽  
pp. 186-195
Author(s):  
Ming-Yuan Zhang ◽  
Fu-Kang Tsou ◽  
Xue-Jun Chen ◽  
Shih-Jiun Chen
Keyword(s):  
Wind Tunnel ◽  
Experimental Technique ◽  
Film Cooling ◽  
Ludwieg Tube

CFD Evaluation and Experiment Test of the Running Time of the Ludwieg Tube Quiet Wind Tunnel

2019 ◽  
pp. 221-230
Author(s):  
Junmou Shen ◽  
Ying Zhang ◽  
Dan Wang ◽  
Ruiqu Li ◽  
Jian Gong
Keyword(s):  
Wind Tunnel ◽  
Running Time ◽  
Ludwieg Tube

scholarly journals Starting Process of a Supersonic Ludwieg Tube with a Downstream Valve

1978 ◽  
Vol 21 (161) ◽  
pp. 1610-1617 ◽  
Author(s):  
Kazuyasu MATSUO ◽  
Shigetoshi KAWAGOE ◽  
Tatsunori OGAWARA
Keyword(s):  
Ludwieg Tube ◽  
Starting Process

Preliminary Tests of High Speed PIV Measurements in a Ludwieg-Tube Supersonic Wind Tunnel

2007 ◽  
Author(s):  
Khalid Juhany ◽  
A. Darji ◽  
Mohammed Zahrani ◽  
Husam Husieni ◽  
Majed Behairi ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
High Speed ◽  
Supersonic Wind Tunnel ◽  
Piv Measurements ◽  
Ludwieg Tube

Investigation on Hypersonic Inlet Starting Process in Continuous Freejet Wind Tunnel

2014 ◽  
Vol 30 (6) ◽  
pp. 1721-1726 ◽  
Author(s):  
Yi Wang ◽  
Zhenguo Wang ◽  
Jianhan Liang ◽  
Xiaoqiang Fan
Keyword(s):  
Wind Tunnel ◽  
Hypersonic Inlet ◽  
Starting Process
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