航空航天实验室- ENG107

面积:1357英尺²
导演:布莱恩·安德拉德
Courses Served: AE160, AE162, AE164, AE168, AE262, AE264, AE266

亚音速空气动力学

目的:
Provide students with experiments in basic flow measurements and visualization. 这些 include pressure 分布s on airfoils, lift and drag measurements of wings and other aerodynamics bodies, boundary-layer measurements, as well as longitudinal and 飞机航向稳定特性. 流可视化包括研究 of high-angle-of-attack flow patterns around airfoils, conical bodies and delta wing 飞机.

现有的车站 & 主要设备

AEROLAB公司:教育风洞系统

性能规格:
空速范围:每小时10英里.5 m/s)到145+ MPH (65 + m/s)
乱流等级:小于0.2%
雷诺数(每英尺):1.4 × 106 /英尺

组件:
• Data Acquisition System(DAS), Display and 控制 System (DAC)
• National Instruments hardware and LabView software
• Capable of monitoring: force/moment balance output, pressures, model angle of attack
•戴尔台式电脑
•3分量力/力矩杆平衡
• Drag model set: teardrop, backward cup, forward cup, circular flat plate, and sphere
•压力气缸
•克拉克Y-14翼型
•压力翼
•尾流耙
•带有可调节板条和襟翼的机翼
•1:48比例的F-16模型
•皮托管静态探头
•偏航探头
• Boundary layer flat plate and 10-tap total pressure probe
•湍流球
•多柱压力计
•压力传感器阵列

标准操作程序

亚音速风洞实验

AE160 -空气动力学I
1. Study of aerodynamic drag as a function of shape (teardrop, backward cup, forward 杯状、圆形平板、球体等.)和雷诺数.
2. Study of airfoil drag as a function of angle-of-attack 和雷诺数 using 尾迹穿越(动量定理).
3. 平板边界层的研究:层流与层流. 湍流边界层，边界 layer transition, boundary layer thickness, boundary layer velocity profiles.

AE162 -空气动力学II
4. Study of the pressure 分布 on a circular cylinder.
5. Study of the pressure 分布 on an airfoil as a function of angle-of-attack 和雷诺数. Calculation of airfoil lift by integrating the surface pressure 分布.
6. Study of airfoil lift and drag as a function of angle-of-attack 和雷诺数 使用直接测量(力平衡系统).
7. Study of airfoil aerodynamic characteristics with high lift devices (leading edge 板条和劈瓣).
AE168 -航空航天飞行器动力学 & 控制
8. Study of the static longitudinal and directional stability characteristics of an f - 16的模型.

Rolling Hills研究公司
水隧道型号0710

性能规格:
尺寸:长=112英寸，宽=46英寸，高=47英寸
容量:105加仑
Test Section: W=7in, H=10in, L=18in Down Stream Window: 7in x 9.5in
流速:2至5英寸./秒.
Turbulence Intensity: <0.5%的均方根

组件:
离心泵:1台.5hp 115VAC 60Hz 16A(不锈钢)
染料注射系统(加压，三色)
控制面板
Models: 2D airfoil, conical body, delta-wing 飞机

水洞实验

AE160 -空气动力学I
 
1. Flow visualization studies on airfoil, conical body, and delta wing 飞机. 附加 / separated flow, steady / unsteady flow, 2-D / 3-D flow, observation of vortex formation 和破裂.

超音速空气动力学

目的:
Provide students with experiments in supersonic flow and familiarity with instrumentation and data acquisition software (LabVIEW), schlieren / shadowgraph techniques for shock and expansion waves visualization, nozzle flow characterization, intrusive pressure and temperature measurements for free-stream flow characterization, measurement of aerodynamic forces acting on bodies submerged in supersonic flows and comparison with 理论模型.

超音速风洞设施
(开发)

性能规格:
自由射流和封闭试验段模式.
Operation at different Mach numbers by exchanging nozzle sections.
马赫数范围(自由喷射模式):从2到3.
Mach Number range (closed test section mode): from 2 to 4.
Reynolds Number per unit length range (free-jet mode):
3.1×107/foot到8.9×107 /脚.

组件
•空气压缩机.
• Two high-pressure air receivers (max operating pressure: 550psi).
• 控制 Valve for steady state operation of the facility.
• Pressure transducers for the measurement of tank, plenum and test section pressure.
• Thermocouples for the measurement of plenum and in-stream temperatures.
• Pressure scanner for the simultaneous measurement of the pressure along the length 从喷嘴或流内耙.
• National Instruments Data Acquisition System and LabView software for the operation of the wind tunnel control valve and for monitoring pressures and temperatures.
• Z-type schlieren system for the visualization of shock and expansion waves and local 马赫数计算.
•耙压力和温度探头.
• Wind tunnel models: wedges, c一个s, diamond-shaped airfoils.

标准操作程序

超音速风洞实验

AE 164 -空气热力学
1. Visualize the flow around sharp and blunt bodies using a Schlieren system.
CLO-1: Compare the shock wave pattern on sharp wedges with the 解决方案 of the oblique 激波方程.
CLO-2: Compare the shock wave around c一个s at zero angle of attack with the Taylor-Maccoll 解决方案.
CLO-3: Visualize the formation of the shock around blunt bodies and understand the 船首激波下游流动的复杂性.

2. Characterize a nozzle flow at different exit Mach numbers in the free-jet configuration using the Schlieren system and the pressure scanner.
CLO-1: Observe and quantify the underexpanded, perfectly expanded and overexpanded 喷嘴的州.
CLO-2: Observe expansion and shock wave patterns in the three cases. CLO-3:估计 the local Mach number through analysis of Schlieren data images.

3. Design, build and validate of supersonic in-stream pressure and temperature probes 通流表征.
CLO-1: Describe and quantify the basic design constraints for supersonic flow probes (大小、几何形状、响应时间).
CLO-2: Understand the measurement lag due to the use of small-sized tubing and finite-size 热电偶电线.
clo3:描述自由流的特性.

4. Evaluate the drag and lift coefficients on diamond-shaped airfoils submerged in 超声速流动，并与现有模型进行比较.
CLO-1: Measure the static pressure on the surface of the models using a pressure scanner.
CLO-2: Compare experimental results with shock/expansion theory.