Seat No.: Enrolment
GUJARAT TECHNOLOGICAL UNIVERSITY
DIPLOMA ENGINEERING SEMESTER VI • EXAMINATION- SUMMER 2018
Subject Code: 3360101 Date: 28-04 2018
Subject Name: AIRCRAFT PERFORMANCE STABILITY
Time: 10:30 AM TO 01:00 PM Total Marks: 70
Instructions:
1. Attempt all questions.
2. Make Suitable assumptions wherever necessary.
3. Figures to the right indicate full marks.
4. Use of programmable Communication aids are strictly prohibited.
5. Use of only simple calculator is permitted in Mathematics.
6. English version is authentic.
Q.1
Answer any seven out of ten.
14
1.
What is Indicated Airspeed and True Airspeed?


2.
Explain Critical Mach no. with proper example.


3.
What is called Steady level Flight? Explain.

4.
Described Troposphere of earth in short.

5.
Define Limit Load Factor and Ultimate Limit Load Factor.


6.
What is called Star board and Port board? Explain with figure.


7.
Draw CD vs CL graph with proper nomenclature.

CD vs CL
8.
Give the Definition of "Endurance of Aircraft".


9.
Described the function of Flaps of an aircraft.


10.
What is called Aerodynamic Center of an aircraft? Define.


Q.2

Draw Temperature vs Altitude Plot for International Std Atmosphere.
03


vs

OR

Short note on "Gliding Flight"
03




Explain Absolute Ceiling service ceiling for an aircraft.
03



OR

Define Airplane Axis system and moment with neat sketch.
03




Short note on "Drag Polar"
04



OR

Short note on "Primary Control surfaces" of an aircraft.
04




Derive Relation Between Local Gravitation acceleration Universal Gravitation acceleration
04



OR

What is called canard? Explain types of canard.
04



Q.3

Explain Static Margin.
03
3



OR

What is called Drag divergence Mach no.? Explain with example.
03




What is static stability? Explain with example.
03



OR

Derive equation for Rate of Climb for Aircraft
03




Explain Horizontal turn Flight and derive its equation.
04



OR

Air(Ideal flow) flowing in a wind tunnel has pressure, Temperature are
04
1.4 atm, 50 C respectively. Find the air density and specific volume for this Ideal Air flow.
atm 1.01 x 105


X


Derive Endurance formula for Jet powered aircraft.
04



OR

Derive Equation of Minimum Thrust for Steady level Flight.
04



Q.4

Draw V-n Diagram for Flight Envelop with proper labeling.
03


V-n

OR

Explain types of atmosphere.
03




Derive minimum Power Required condition for steady level flight.
04



OR

Prove that minimum Thrust required condition for Steady level flight is
CD,0 CD,i
04

CD0 =CDI


Air (Ideal flow) flowing in a wind tunnel has Pressure, Density and Mach no are 0.35 atm, 0.982 kg/m3, 0.3 respectively. Find the air Temperature and velocity of this Ideal flow.
atm 1.01 x 105
07

atm,
atm x

Q.5

Why the Swept back wing is required for a fighter aircraft? Explain in detail.
04





Established the Relation Between Geopotential altitude Geometric altitude.
04




Short note on "SecondaryControl surfaces" of an aircraft.
03




What is dynamic stability? Explain with example.
03