TY - GEN
T1 - Experimental Results for a Straight Tapered Flying Wing with Bell-Shaped Lift Distribution
AU - Richter, Jonathan S.
AU - Woodring, Jason B.
AU - Agarwal, Ramesh K.
N1 - Funding Information:
The Authors would like to thank several individuals who helped with this paper and made the construction of the Biom possible. The authors would like to especially thank Kevin Hainline. Without his hundreds of hours of mentoring and aid, none of this would have been possible. Additionally, the authors would like to thank Luke Solondz for his assistance and technical expertise as well as the entire WUDBF Team for support. Some of the financial support for this work was provided by Missouri NASA Space Grant, which is gratefully acknowledged.
Publisher Copyright:
© 2022, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2022
Y1 - 2022
N2 - A glider using a bell shaped lift distribution and a proverse yaw control scheme was designed to gather atmospheric data on Mars. The flight conditions for the glider on Mars were Mach 0.6 and a Reynolds’s number of approximately 25000. The glider was designed with no vertical surfaces to allow for efficient stacking of multiple gliders. The glider’s airfoils were designed in XFoil to achieve a glide ratio of approximately 10 while maintaining control authority within angles of attack of-5 to 7 degrees. Under these conditions, the glider would achieve a range of approximately 50 km if launched from 5 km in altitude. The control scheme was validated in AVL, and AVL was used to find the optimal size for all control surfaces. A preliminary prototype of the glider was built and flown. It could carry a payload 1.5kg on Mars and 0.5kg on Earth. In flight testing the model was verified to be controllable and stable with no vertical surfaces.
AB - A glider using a bell shaped lift distribution and a proverse yaw control scheme was designed to gather atmospheric data on Mars. The flight conditions for the glider on Mars were Mach 0.6 and a Reynolds’s number of approximately 25000. The glider was designed with no vertical surfaces to allow for efficient stacking of multiple gliders. The glider’s airfoils were designed in XFoil to achieve a glide ratio of approximately 10 while maintaining control authority within angles of attack of-5 to 7 degrees. Under these conditions, the glider would achieve a range of approximately 50 km if launched from 5 km in altitude. The control scheme was validated in AVL, and AVL was used to find the optimal size for all control surfaces. A preliminary prototype of the glider was built and flown. It could carry a payload 1.5kg on Mars and 0.5kg on Earth. In flight testing the model was verified to be controllable and stable with no vertical surfaces.
UR - http://www.scopus.com/inward/record.url?scp=85135044935&partnerID=8YFLogxK
U2 - 10.2514/6.2022-3585
DO - 10.2514/6.2022-3585
M3 - Conference contribution
AN - SCOPUS:85135044935
SN - 9781624106354
T3 - AIAA AVIATION 2022 Forum
BT - AIAA AVIATION 2022 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA AVIATION 2022 Forum
Y2 - 27 June 2022 through 1 July 2022
ER -