Aircraft Climb Performance Analysis – Engineering Assignment Help

Aircraft Climb Performance Analysis – Engineering Assignment Help
Assignment Task

Assignment Description

The airline company that you work for is considering the use of using de-rated power setting for its current engines. As a member of its engineering team you have been asked to produce a report which analyse and evaluate the aircraft’s/engine climb thrust and fuel performance so that it can be considered by the airline management.

The report will require you to source the following technical information for its 737-800 aircraft:

Wing span (b)

Wing area (A)

Max. take-off mass (MTOW = W0)


CLTO (max. take-off lift coef.)

CD0 (zero-lift drag coef.)

K = 1/eAR (lift-induced drag factor)

From the researched information and using the engine data provided in the following table, calculate the following data by use of MATLAB (or MATLAB equivalent) and produce graphs to support your analysis:

Aircraft ceiling

Aircraft climb angel at different phases of the climb

Aircraft drag produced at different phases of the climb

Power available

Power required

Excess power

Time to climb

Speed at cruise

Fuel consumed to climb

N.B The Engine data is supplied in a separate file.

In undertaking the analysis of the data and graphs produced, these should be compared against data obtained from programming your proposed climb profile into the flight simulator for the two different engines. Your analysis should comment on any differences discovered between the theoretical calculations and practical observation along with any reason why they may have occurred.

The flight sim testing:

Programme required data form sourced data into Flight Simulator

Carry out a standard climb for two different engine ratings to aircraft ceiling at 250 knots IAS.

Monitor and record aircraft parameters you deem important, e.g., AOA, fuel flow, rate of climb, TAS on climb-to-cruise levels, etc.

The analysis from the data and graphs should indicate:


ISA (International Standard Atmosphere) implication

Computationally analysing the aircraft’s performance on climb configuration

Computations of aircraft ceiling, ,CL, CD, Uclimb, rate of climb Vc, angle of climb , on climb-to-cruise levels

Graphic plots: (Vc vs h), (, vs h), (mf, vs, time), (Uclimb vs t/h), (power available vs power required)

The assumptions made for the process of calculations

The marking scheme breakdown is as follows:

Define the absolute ceiling of the selected aircraft – compare you result with the aircraft’s declared data. Provide comments on both declared and your data

Discuss the configuration of the selected aircraft in terms of power setting (available and required) to achieve optimal climb performance

Calculate D, CL, Uclimb, Vc, , fuel to climb (describe your computational approach)

Result’s graph plots: (vc vs h), (, vs h), (mf, vs, time), (Uclimb vs h), (power available vs power required); graphs must be presented with title and number, curve’s legend, axis title, units, and scaling

Analyse each plot and concluding remarks

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