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Development of Testbed Procedures for Aerodynamic Model Measurements in Parks College Low-Speed Wind Tunnel.

紀錄類型:	書目-語言資料,手稿 : Monograph/item
正題名/作者:	Development of Testbed Procedures for Aerodynamic Model Measurements in Parks College Low-Speed Wind Tunnel./
作者:	Glowacki, Jeremy T.
面頁冊數:	1 online resource (165 pages)
附註:	Source: Masters Abstracts International, Volume: 84-11.
Contained By:	Masters Abstracts International84-11.
標題:	Civil engineering. -
電子資源:	click for full text (PQDT)
ISBN:	9798379572211

Development of Testbed Procedures for Aerodynamic Model Measurements in Parks College Low-Speed Wind Tunnel.
Glowacki, Jeremy T.

Development of Testbed Procedures for Aerodynamic Model Measurements in Parks College Low-Speed Wind Tunnel. - 1 online resource (165 pages)

Source: Masters Abstracts International, Volume: 84-11.

Thesis (M.S.)--Saint Louis University, 2023.

Includes bibliographical references

Parks College of Engineering has a long history of being on the forefront of aerospace engineering studies. In an effort to expand upon their abilities to teach their students, a large, low-speed wind tunnel was purchased from Aerolab in 1967. The purchase greatly expanded the college's capacity for research and education and has since been a staple in their curriculum. At first, the wind tunnel was verified and documented carefully. Over the last several decades modifications and updates to the various subsystems were made but were not as well documented as the original system was. Due to this much of the tunnel was left in an unverified state causing its reliability, accuracy, and precision to be questioned. One such place where the wind tunnel accuracy was questioned was in the student's lab experiment during Aerospace Lab. The students consistently noted poor drag readings and the inability to see changes in the data according to model changes. To address these issues and reverify the wind tunnel, a geometrically scaled P-51D Mustang airplane was designed, manufactured and tested in the wind tunnel. The model was 3D printed out of plastic and designed using Solidworks and featured the ability to change its configuration through the use of specially printed control surfaces. The elevator, rudder and ailerons had two different configurations, one deflected at 10 degrees and the other undeflected which allowed for a variety of different measurements to be taken. Additionally, a no horizontal stabilizer configuration was made to allow for an understanding of the wing airfoil's pitching behavior. The Xflr5 aerodynamics model was used to create theoretical lift and drag data for the clean configuration which could be later compared to testing to determine a rough estimate of the overall accuracy of the system in capturing the behavior of the model in the wind tunnel. Testing consisted of running the model at speeds of 30, 40, 55 and 70 mph in the wind tunnel through angle of attack sweeps from -8 to 16 degrees. Data that was collected from the pyramidal balance included the three aerodynamic forces (lift, drag and side force) and the three aerodynamic moments (pitch, roll and yaw) along with measurements for the angle of attack and the temperature in the wind tunnel. During these tests a number of observations were made on the subsystems that ultimately led to the recalibration of the balance and manometer board. These recalibration processes uncovered more issues with the balance and data acquisition program that required attention before testing and analysis could be continued. These issues included problems with the pitch strut, locational issues with model placement caused by pitch arm location and lack of ability to determine sideslip angle, incorrect values in the decoupling matrix, and issues with the data recording program. Through the recalibration process, design and building of various apparatuses and the thorough documentation of the data acquisition program the tunnel entered a partially reverified state where the data could be analyzed with increased confidence. Testing of the P-51D produced results looking at the precision of the balance recording system as well as various aspects that affected the data such as the sample size, sample rate, model placement and inertial shift interference. Based on these tests this system appears to be highly precise and consistent with its measurements as the data shows the correct trends throughout all the tests with low levels of uncertainty overall. However, the drag measurements were found to be highly inaccurate because much of the drag data was negative in value. Additionally, the beta sweeps provided strong evidence that the system can accurately show sideslip angle if the correct calculations are used. The sample size tests showed that the system behaves cyclically and the precision and accuracy of the data was not highly sensitive to sample size. Overall, the data shows that testing with this system can produce quality results for a model of this size and could be used for further research and study. With more modification and updates to certain systems, the tunnel could likely produce highly accurate results that could support high level research in the future.

Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2024

Mode of access: World Wide Web

ISBN: 9798379572211Subjects--Topical Terms:

561339
Civil engineering.
Subjects--Index Terms:

AerolabIndex Terms--Genre/Form:

554714
Electronic books.

Development of Testbed Procedures for Aerodynamic Model Measurements in Parks College Low-Speed Wind Tunnel.
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