Project Details

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Small Dynamic Wind Tunnel

Company: Lockheed Martin

Major(s):
Primary: ME
Secondary: EE
Optional: CMPEN, CMPSC, ESC

Non-Disclosure Agreement: NO

Intellectual Property: NO

Aircraft rely on numerous sensors to monitor the airflow characteristics around the control surfaces and fuselage during operation. While the pitot-static tubes are the most visible, near the aircraft nose, other sensors are used during testing and operation to monitor air pressure and flow. Kiel probes are used to measure the total pressure of a flow with high accuracy over a wide range of flow angles. The ability to measure pressure in a fluid stream where flow direction is unknown or varies with operating conditions is useful for UAV/UAS. The scope of this project is to design and develop a wind tunnel that can be used to calibrate Kiel probes. The wind tunnel shall include electromechanical controls to change the roll, pitch, and yaw of the sensor relative to the primary airflow. After construction of the wind tunnel, rough dimensions 36"x24"x24", the team will run tests to quantify the quality of the airflow. Kiel probes will then be provided to the team to record signal values at various orientations relative to the flow. After demonstrating system performance, the team & sponsor will review options to optimize tunnel design for operator safety to deliver to Lockheed Martin for use in our Innovation Garages. This project will be a multidisciplinary project requiring team with software, electrical, testing, and mechanical skills to be successful.