The test section is where models are placed so that they will be exposed to the desired airflow generated by the wind tunnel to assess their performance under controlled conditions. The test sections must be configurable for many types of models (aircraft, rockets, engines, etc.) and will need to allow many types of measurements besides the standard pressure/lift/drag measurements. Data on acoustics, bending modes, and temperature gradients is of high interest in modern design trades. Specialized test sections are sometimes needed to capture data sets with high accuracy. Installing models and optimizing test sections for different types of measurements is time-consuming and reduces the amount of testing that can be done in a facility. The NASA Unitary Plan Wind tunnel! is an example of a facility that can direct its airflow to three separate test sections to increase facility throughput. Interchangeable test sections may be even more efficient. How would you design a wind tunnel facility with one or more test sections that can be efficiently and rapidly reconfigured by multiple test teams so that facility utilization can be maximized? While new models are being installed and integrated into the test section, the wind tunnel is not running which results in reduced utilization. Operational efficiencies are an area of improvement in the design of the facilities’ test section which could increase performance and cost effectiveness. The ability of the test team to rapidly swap out models is a lot like the capabilities of a race car pit crew to the overall efficiency of a wind tunnel. This contest is in support of a NASA concept study called the “New Wind Tunnel Landscape.” The goal of the study is to develop several options to support the future wind tunnel testing required in the next 20-50 years. The test section design is one aspect of what might enhance the effectiveness of future wind tunnels. In addition to swapping out models, researchers may want to configure the test section itself for different test objectives (e.g. sound abatement for acoustic measurement accuracy, optical windows for laser metrology on structural dynamics).
Award: $7,000 in total prizes
Open Date: June 6, 2022
Close Date: July 18, 2022
For more information, visit: https://grabcad.com/challenges/nasa-challenge-new-transonic-wind-tunnel-test-section