كلية الهندسة
College of Engineering
جامعـة قـطـر QATAR UNIVERSITY
1. Objective:
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2. Background:
MECH 416 - Aircraft Design
Assignment No (01): Aircraft Performance Analysis
3. Task:
Understanding fundamental performance parameters
Applying equations to calculate performance characteristics
Interpreting and analysing performance results.
Aircraft performance analysis is a critical component of aircraft design. It involves the
evaluation of various factors such as aerodynamics, propulsion, and structures to determine
how well an aircraft will perform under different conditions. The goal of performance analysis
is to ensure that the aircraft meets its intended design requirements and is safe, efficient, and
cost-effective to operate. It also allows for the optimization of the aircraft's performance, which
can lead to improved fuel efficiency, increased range, and reduced maintenance costs. Overall,
performance analysis is an essential part of aircraft design, as it ensures that the aircraft meets
the needs of its intended users and performs reliably and efficiently.
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The data for the small single-seat home-built jet airplane are as follows:
Wing span: 5.2 m.
Wing planform area: 3.5 m².
Gross weight at take-off: 4270 N.
Fuel capacity: 55gal. (1 gallon of JP-4 ≈ 3.08 kg)
Power plant: one French-built Microturbo TRS 18 turbojet engine with maximum
thrust at sea level of 898.5 N and a specific fuel consumption of 1.3 N/(N.hr)
the drag polar for this airplane can be estimated to be:
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In this assignment, you will make a Performance analysis for small single-seat home-built jet
airplane, using the following information and requirements:
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جامعة قطر
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Cp = 0.02 +0.062C²
Page 1 of 3 كلية الهندسة
College of Engineering
جامعة قطر QATAR UNIVERSITY
a. the maximum velocity at sea level and
b. the maximum velocity at 3.048 km.
1. Plot the thrust required and thrust available curves at sea level, and from these curves
obtain the maximum velocity at sea level.
2. Plot the thrust required and thrust available curves at 3.048 km, and from these curves
obtain the maximum velocity at 3.048 km.
3. calculate analytical (directly)
Vmax
1/2
√(TA)
[(TA)max/w] (W/s) + (W/s) √ [(T₁)max/w] -4CD,K
Poo CDo
Max Thrust available at altitude can be estimated by using this Equation
(T^) max = (T₁). [206
● Compare the result in 3 with those from 1 & 2.
4. calculate
2
6. Use the analytical results to calculate directly
جامعة قطر
a. The maximum value of CL/ CD
b. The maximum value of C₁¹/2/CD
c. The maximum value of C₁³/2/CD
d. The velocities at which they occur at sea level
e. The velocities at which they occur at 10,000 ft
5. Plot the power required and power available curves at sea level. From these curves,
estimate the maximum rate of climb at sea level.
a. Maximum rate of climb at sea level and the velocity at which it occurs.
Compare with your graphical result from 5.
b. Maximum climb angle at sea level and the velocity at which it occurs.
7. Consider our Aircraft flying at 10,000 ft. Assume a sudden and total loss of engine
thrust. Calculate
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a. the minimum glide path angle,
b. the maximum range covered over the ground during the glide, and
C. the corresponding equilibrium glide velocities at 10,000 ft and at sea level.
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College of Engineering
جامعة قطر QATAR UNIVERSITY
10. Using the analytical approach described in Lecture Note 6 page 12, calculate the
minimum time to climb to 10,000 ft.
8. Plot the maximum rate of climb versus altitude. From this graph, estimate the service
ceiling.
9. analytically calculate the service ceiling, and compare this result with the graphical
solution obtained in 8.
11. Estimate the maximum range at an altitude of 10,000 ft. Also, calculate the flight
velocity required to obtain this range.
12. Estimate the maximum endurance.
4. Requirements:
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5. Grading Rubric:
جامعة قطر
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Choose either MATLAB or an Excel spreadsheet for your analysis.
Use scientific principles and relevant equations to perform the calculations.
Document your code with clear comments explaining each step and the formulas used.
● Accuracy: Correctness of calculations.
Analysis: Ability to interpret results and draw meaningful implications (e.g., how do
the results compare to typical aircraft of that class, or inform aircraft design choices).
Clarity: Presentation of calculations and explanations.
Page 3 of 3
