and include any assumptions that have to be made to get this condition. Finally, discuss in a

few sentences why a high-performance aircraft needs a capability for a maximised RoC, and

give an example of the highest RoC that you can find.

[10 marks]/nQ1. Explain in your own words why the stall speed of an aircraft is given by:

W

√ZPSC₁

Define all terms.

Vstall

v=

Q2. An aircraft has a maximum lift coefficient of 1.65 with the flaps and slats up. The stalling

speed for that level of trim is expected to be 99 m/s. The weight of the aircraft in cruise at this

time is required to be 50500 Lbf, and the cruise altitude is 11.5 km. Find the wing area required

to

the aircraft

these conditions. You may refer

https://www.pdas.com/atmosTable2S1.html for any further data you may require. Show any

rearrangements of equations used and also show all arithmetical working.

support

under

to

[10 marks]

W

Q3. Assume that an aircraft is climbing at a fixed angle of ascent and then proceed to show

that the RoC is given by:

'L_max

1

ZPS

¹/2

[10 marks]

T-1/2 (CDo + KC²)

CL

W

(Ceo + KCB))

3/2

C₁

Start your analysis using the RoC defined by v = V sin p. Define all terms used and show all

steps in the analysis.

Show then that the condition for maximum RoC is:

T

kCZ +CL-3CDo = 0

W