6 points, SCA Band 2, 0.125 EFTSL
Undergraduate - Unit
Refer to the specific census and withdrawal dates for the semester(s) in which this unit is offered.
Department of Mechanical and Aerospace Engineering
- Second semester 2018 (On-campus)
On completion of this unit students will have an understanding of the key elements of aircraft performance analysis as used in aerospace vehicle design. A student project involving the initial design stages of a flight vehicle will integrate these studies. Various characteristics of aircraft performance and their design implications will be examined including whole-aircraft drag polar, power plant characterisation, thrust required in level flight, maximum speed estimation, minimum speed and high-lift devices, rate of climb, gliding, range, endurance, accelerated flight, structural limitations on performance, design for longitudinal and lateral stability. Mission analysis and preliminary weight estimation based on a design concept will be examined together with the aerodynamic synthesis to satisfy performance requirements, power plant selection, overall vehicle layout and balance. Trade-offs as a necessary part of the design will be apparent to students on completion of this unit.
On successful completion of this unit, students should be able to:
- Produce a preliminary aircraft weight estimate from a supplied mission profile and aircraft category
- Generate initial estimates of aircraft wing area and propulsion capacity given a supplied aircraft category and mission profile
- Choose an appropriate layout of aircraft elements given supplied aircraft category and mission profile
- Produce a dimensioned and appropriately labelled three-view line diagram of an aircraft layout
- Estimate aircraft drag polar coefficients from a given geometry and mission profile using a drag-buildup method
- Choose and size an appropriate wing airfoil and high-lift system for a given aircraft category and performance requirement
- Comprehend and apply aircraft performance analysis particular to the choice of aircraft wing loadings and thrust (or power) to weight ratios in order to meet specified performance constraints
- Estimate aircraft component group weights from available correlations, and to incorporate these into a refined weight estimate for a given aircraft layout, size and mission profile
- Arrange aircraft components in order to place the centre of gravity in a desired location
- Choose and locate landing gear components appropriate to the aircraft category and weight
- Size and locate tail surfaces to achieve a desired static longitudinal stability and control effectiveness
- Provide a scaled, dimensioned and appropriately labelled three-view line diagram of an aircraft
- Understand the concepts of simple design optimisation via investigation of design choice alternatives
Continuous assessment: 70%
Final Examination (2 hours): 30%
Students are required to achieve at least 45% in the total continuous assessment component and at least 45% in the final examination component and an overall mark of 50% to achieve a pass grade in the unit. Students failing to achieve this requirement will be given a maximum of 45% in the unit.
3 hours lectures, 4 hours practice sessions or laboratories and 5 hours of private study per week.
See also Unit timetable information