Flight Performance & stability

UFMFFK-15-2 Flight (2020/21)
Flight Coursework Specification – RESIT
Flight Performance and Stability
Submission Date 3 AUG 2021 at 14h00
Marks Weighting 100% of module
Submission Method Electronic via BB
Deliverables & Format Engineering report
Grade & Feedback: 20 AUG 2020
Group Sizing Individual
Tutors Sean Tuling, Vilius Portapas
Issue Version & Date 1.0, 17 JUN 2020
1. Resit Introductory Notes
The coursework specification documents the requirements for the resit period
(assessment period 3) for the academic year 2020/2021. Depending on your resit
circumstances different criteria apply.
Failure Codes #RA, #RB : Different options exist for this failure code depending on
what why you have failed either component. FOR ALL CASES CONSULT WITH THE
MODULE LEADER FOR YOUR MOST APPROPRIATE OPTION. These will range
from attendance of the missed final viva from the first sit, submission of an individual
sub-report from the first sit, to completion of the engineering report meeting the
requirements specified in the subsequent sections of this specification.
Failure Codes #RALL, #F : Completion of the engineering report meeting the
requirements specified in the subsequent sections of this specification.
IF IN DOUBT, CONSULT WITH THE MODULE FOR YOUR MOST APPROPRIATE
OPTION 2. Learning Outcomes
Following the successful completion of this coursework you will be able to
1. Analyse the performance and static stability of an aircraft
2. Determine the characteristics of the dynamic primary modes of an aircraft
3. Operate a flight simulation package
4. Process flight test data
Secondary learning outcomes are report writing and programming skills development.
Even though the reporting component only accounts for a small portion of the overall
mark report writing is a requisite skill for engineers. For almost all industry deliverables
and assessment methods the duty remains on the author(s) to demonstrate they have
met the specifications and to communicate their competence. Your ability to
communicate clearly and effectively will affect your grade.
3. Background/Context
Successful design of aircraft require the analysis of the performance and stability of
the aircraft so that the design process can meet operational and regulatory
requirements. Part of the design of the aircraft is normally driven by key performance
requirements such as climb and range, whilst stability and manoeuverability tend to
be driven by acceptable handling requirements.
4. EV-97-O Observation Platform Design
Your company has taken on the task to assess whether the requirement to use the
EV-97 light aircraft as an observation platform, designated the EV-97-O, is feasible
from a performance and static stability perspective. The ‘passenger’ will operate the
observation pack when a flight requires this functionality, though the aircraft is required
to be operated on other missions without employing the observation pack.
Additionally, the aircraft may be operated when the observation pack is removed for
maintenance, but the upgraded engine and wing modifications remain. The modified
design is intended to maximise the range/endurance. No structural analysis shall be considered. The standard EV-97 using the Rotax 912ULS is to be upgraded using the
components in Table 1.
Table 1. EV-97-O upgrade components
Component Weight
[kg]
(x,y,z)** c.g.
from datum
[m]
Rotax 915 141hp engine ∆ 28* (0.5,0,0)
Wing-tip extensions extending the wingspan by 1m
(wing chord is the same as original aircraft)
5 (0.225,0,0)
Observation payload pack 24 (-2.0,0,0)
* The weight is the difference between the original engine and the upgraded engine
* x is defined positive in the forward direction from the perspective of the pilot. A
positive value indicates the component is forward of the datum.
The propeller efficiency characteristics are a function of advance ratio described as
follows:-
= 3.7567 + 1.343
ଶ − 15.02
ଷ
where
=

and is the forward velocity, is the rotational velocity in rps and is the diameter of
the propeller.
The thrust coefficient is
் = 0.04013 + 0.05058 − 0.2031
ଶ
The thrust is related to the thrust coefficient by
= ଶ
ସ்5. Requirements
You are required to
1. Analyse the theoretical performance of the EV-97-O for the various flight
phases in the context of the design process, including take-off, climb, cruise,
descent and landing.
2. Analyse the weight and balance of the EV-97-O
3. Analyse the longitudinal stick-fixed and stick-free static stability of the EV-97-O
4. Analyse the primary dynamic modes for the standard EV-97 aircraft (NOT the
EV-97-0) using the following methods:-
a. Analytical (characteristic roots/eigenvalues)
b. Numerical models in the time domain
c. Flight Test
5. Perform the flight simulation laboratory by acquiring and processing flight testlike data for the PA-28 using simulations from the X-Plane simulator