July 18, 2018 – Reston, Va. – The American Institute of Aeronautics and Astronautics (AIAA) Foundation announced the winners of its 2017–2018 AIAA Foundation Engine Design Competition on July 11 at the AIAA Propulsion and Energy Forum in Cincinnati, Ohio. The 2017–2018 Engine Design Competition’s goal was to design a “Next Generation Supersonic Transport.”
The winning teams are:
1st Place – Beihang University, China
- Team Name: The Little Boys
- Student Team members: Yingjun Wang, Mingha Guo, Yu Hu
- Faculty Advisors: Dr. Min Chen
2nd Place – TOBB University of Economics and Technology, Turkey
- Team Name: ETU-V TULPAR
- Student Team members: Veli Can Üstündag, Çağdaş Cem Ergin, Baran Íper, Onur Tan
- Faculty Advisor: Prof. Sitki Uslu
3rd Place – Warsaw University of Technology, Poland
- Team Name: Totally Incredible Technical Solution
- Student Team Members: Damian Maciorowski, Karol Kozdrowicz, Maciej Spychata, Karolina Pazura
- Faculty Advisor: Dr. hab. Inz. Ryszard Chachurski
Candidate Engines for a Next Generation Supersonic Transport – Request for Proposal
Sponsored by:
Schedule
Engine Design Competition dates
- Letter of Intent submitted via – 14 February 2018 (11:59 p.m. Eastern Time)
- Proposal submitted via – 16 May 2018 (11:59 p.m. Eastern Time)
- Round 1 evaluations completed – 30 June 2018 (11:59 p.m. Eastern Time)
- Round 2 presentations at
Background
New engine designs are solicited for the next generation supersonic transport. Entry into service is expected to be 2010 – 2025. This current solicitation is motivated by NASA’s National Research Announcement (NRA) back in 2006 (NNH06ZEA001N, Amendment 6, Task 4.7) for a supersonic transport vehicle. The NRA is calling for an aircraft that is a generation beyond the supersonic business aircraft that is currently being considered and smaller than the supersonic airliners of past NASA programs (i.e. High Speed Civil Transport). The baseline propulsion system is based on the engine modeled in NASA/CR-2010-216842. The candidate engines must demonstrate at least 5% improvement in TSFC (at specified thrust levels) and substantiate weight savings. Furthermore, both cruise emissions goal and noise constraint (represented by exit jet velocity) are imposed.
Data for a generic baseline model of the baseline power plant is supplied. Responders should use the provided typical, multi-segment, mission to address the design improvements, especially for design point and off-design engine operations. The performance and total fuel consumption of the candidate engine should be estimated for critical mission points and stated clearly in the proposal. Special attention should be paid to engine mass, dimensions and integration with the aircraft.
