1. Subsystem Level Design Review

2.  Project Review  System Level Changes ◦ Tail Dragger ◦ Airfoil Change and Discussion  Subsystem Selection ◦ Fuselage Structure ◦ Wing Material ◦ Wing Construction ◦ Landing Gear Selection ◦ Tail Mounting  Aerodynamic Design, Sizing, and Static Stability ◦ Aerodynamic Wing Design and Sizing ◦ Horizontal Stabilizer Sizing and Longitudinal Static Stability ◦ Vertical Stabilizer Sizing and Directional Static Stability ◦ Updated Take-off and landing ◦ Testing Plan

3.  RIT Aero Design Club has been absent from the SAE Aero competition (Regular Class) since 2008 ◦ Prior to 2008, RIT had been inconsistent in participating in the competition annually  Lacking… ◦ Experienced veterans to lead/guide the club ◦ Aeronautical engineering experience/knowledge ◦ Full commitment as students are on co-op for parts of the year ◦ Funding

4.  Deliverables ◦ A functional finished aircraft designed and built to SAE Aero standards ◦ Comprehensive documentation of design, build, and testing methods and processes  Jumpstart the Aero Club ◦ Build competence through sharing experience from the present Senior Design project ◦ Desired State: Aero Design club is able to compete in the SAE Aero Competition annually and be competitive

7.  Objectives targeted from functional decomposition ◦ Aircraft must have enough lift to fly ◦ Aircraft must be stable and controllable ◦ Aircraft must survive landing

11.  More desirable α for takeoff for S1223 airfoil  Support of front landing gear more directly supporting the payload bay  Benefits for meeting our dimensional constraints  Tail strike during landing now a designed for risk  Challenges: ◦ Additional bending stress during takeoff and landing on the tail boom ◦ Propeller strike during landing now more serious risk ◦ E423 airfoil less generous in acceptable range of α

15. S1223 E423 Pro or ConDetail: + Higher C l + Designed for low Re + Cruise α more forgiving for stall characteristics - C mac very high - C D high - Manufacturing challenges Pro or ConDetail: + C mac lower +Easier to trim + Smaller tail allows for more lifting area -Lower C l - Flight conditions outside of traditional flight regime + Thicker trailing edge is easier to manufacture + At a particular angle of attack E423 generates more lift and less drag

17. Truss Platform Keel

18. Foam Balsa 3D-Printed

19. One Piece Two Piece Two Piece w/ Wingbox

21. Bottom Middle Wingbox

23.  Thin trailing edge on S1223 wing configurations has a high risk of snapping  3D printed trailing edges would increase strength without too much of a weight increase

24.  An estimate to get the order of magnitude for expected impact loading  We will want to design for impacts in the range of a thousand pounds

25.  An estimate to get the order of magnitude for expected bolting strength in the fuselage  We should be able to design for considerable strength

26. Aerodynamic Wing Design and Sizing: Parameter Selection

27. Aerodynamic Wing Design and Sizing: Overall Geometry

28. Horizontal Stabilizer Design: Parameter Selection

29. Longitudinal Static Stability Sizing Diagram

30. Preliminary Fuselage Sizing Diagram: Static Stability and Internal Storage Requirements

31. Horizontal Stabilizer Design: Overall Geometry

32. Overall Aircraft Longitudinal Static Stability

33. Vertical Stabilizer Design: Parameter Selection

34. Vertical Stabilizer Design: Overall Geometry

35. Overall Aircraft Directional Static Stability

36. Updated Take-Off and Landing Performance