AERO GATE TOPPER
General Instructions:
- The total duration of the examination is 60 minutes .
- The clock will be set on the server. The countdown timer in the top right corner of the screen will display the remaining time available for you to complete the examination. When the timer reaches zero, the examination will end by itself. You will not be required to end or submit your examination.
- To answer a question, do the following:
Navigating to a Question:
- To answer a question, do the following:
- Click on the question number in the Question Palette to go to that question directly.
- Select an answer for a multiple-choice type question. Use the virtual numeric keypad to enter a number as the answer for a numerical-type question.
- Click on Save and Next to save your answer for the current question and then go to the next question.
- Caution: Note that your answer for the current question will not be saved, if you navigate to another question directly by clicking on its question number.
- You can view all the questions by clicking the Question Paper button. Note that the options for multiple-choice type questions will not be shown.
- Procedure for answering a multiple choice type question:
- To select your answer, click on the button on one of the options
- To deselect your chosen answer, click on the button of the chosen option again
- To change your chosen answer, click on the button of another option
- To save your answer, you MUST click on the Save and Next button
- Procedure for answering a numerical answer type question:
- To enter a number as your answer, use the virtual numerical keypad
- A fraction (eg.,-0.3 or -.3) can be entered as an answer with or without ‘0’ before the decimal point
- To clear your answer, click on the Clear button
- To save your answer, you MUST click on the Save and Next button
- To change your answer to a question that has already been answered, first select that question for answering and then follow the procedure for answering that type of question.
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Which of the following statements are true as altitude increases in troposphere in ISA
An aircraft is crusing at TAS of 7 m/s under ISA conditions, at an altitude density is 0.763kg/m3 . What is the equivalent airspeed (answer in one decimal)
As altitude increases, the minimum drag
The sealevel pressure and temperature are 1.005 bar and 293 K. At unknown altitude in troposphere, the pressure and temperature are 71800 Pa and 263K. find the altitude (in meters) in that location?
The sea level pressure and temperature are 1.005 bar and 293 K. At unknown altitude in troposphere, the pressure and temperature are 71800 Pa and 263 K, is the atmosphere
The rate of climb is measured by
An aircraft has $CD = 0.04+0.059CL^2$ , the glide angle that results in maximum range of power off glide is ------------. (answer in one decimal)
To maintain steady level flight, as altitude increases velocity should
The minimum drag is proportional to
An aircraft has a steady rate of climb of 350m/s at sealevel and 175m/s at 2500m altitude. The time taken for this aircraft to climb from 500m to 3500m altitude is ----------. (neares integer answer)
The minimum drag speed is ------------ times of minimum power speed. (answer in one decimal)
As Weight increases,
The maximum climb angle depends upon
A glider having W=2000N, S=8.0 $m^2$, aspect ratio is 16, e=0.95, $C_{D_0}=0.015$ is launched from a height of 300m. Determine the maximum range and corresponding glide speed.
An aircraft has a level flight stalling speed of 60m/s EAS. As per V-n diagram, what is the minimum speed at which it should be designed to withstand the maximum vertical load factor of 9?
A flying wing with a area of 27.75m2 has a NACA 2412 aerofoil section. The weight of the flying wing is 2270.663 Kg , Oswald lift deficiency factor is 0.95 and aspect ratio is 6. For a level flight at an altitude of 1500m, the relative density is 0.864 and the velocity is 160km/hr. Match the following (i)angle of attack(deg) a)11.29, (ii) induced drag coefficient(x10^-2) b)9.72, (iii)drag(x10^2 N) c)3.29.
For climbing flight the load factor is
A propeller aircraft weighs 50000N and a wing area of 30m2 . The reciprocating engine develops a power of 840 kW at sea level and a adjustable pitch propeller has a efficiency of 0.85. The drag polar of the aircraft is given by CD = 0.025+0.05CL2 and the maximum lift coefficient is 1.75. Determine the maximum and minimum speeds in level flight at sea level.
A glider weighing 5000N and an elliptical wing with a area of 10m2 is required to maintain a glide angle of 3 deg at a forward speed of 50m/s. Assuming CD0 = 0.015, find the aspect ratio of the glider. (answer in one decimal)
A turbojet airplane weighs 450000N and has a wing loading of 1450 N/m2. The drag polar of the aircraft is given by CD= 0.014+0.038CL^2and the maximum lift coefficient is 1.5 and the thrust T=20000 times of relative density. Determine the maximum and minimum speeds in level flight at sea level and at an altitude of 9000m where relative density is 0.3813. What is the absolute ceiling of this airplane? (answer in nearest integer)
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