
Calculating Cruise Flight Performance of Jet-Engine Aircrafts V2.0
by admin in Aerospace , Control Systems & Aerospace , MATLAB Family on April 23, 2019This is the second version of ‘Flight Cruise Performance Calculator for Jet Aircraft’ and also is about a GUI program that calculates Range and Endurance (Flight-Time):
- Range for Fixed Altitude
- Range for Fixed Velocity
- Flight-Velocity that force Fixed-Altitude-Range
- Flight-Velocity that force Fixed-Velocity-Range
- Endurance (Flight Time)
in addition to the other cruise flight performance in the past version, includes:
- Maximum Level Flight Speed
- Minimum Level Flight Speed
- Stall Speed
- Speed Corresponding to Minimum Drag
- Maximum Lift to Drag Ratio
- Absolute Ceiling (Maximum Flight Hight corresponding to Minimum Drag)
- Chart presents: Induced Drag, Zero-Lift Drag, Total Drag and position of Vmin, Vmax and VDmin.
Required Inputs:
To run the program you need to insert the following values:
- Flight Altitude
- Reference Area
- Airplane Weight
- Fuel Weight
- Fuel Consumption
- Engine Thrust
- Zero-Lift Drag Coefficient CDo
- K constant of CL^2 in the drag polar equation
- Maximum Lift Coefficient.
The program gives you the maximum hight, Velocity, Range and Endurance of a given airplane characteristics and the minimum required thrust for this altitude. The code based on Pamadi[1] and Saarlas[2] equations of performance of jet engine aircraft in cruise flight.
Examples you can try with this program:
A jet-engine airplane weighs 45000 N, hold fuels 10000 N, and has a reference area S of 31 m2. The drag polar is given by CD = 0.014 + 0.038CL^2, CLmax = 1.5, and the engine thrust T = 20,000 N, and Engine Specific Fuel Consumption 30 N/N/H. Determine the maximum and minimum speeds in level flight at sea level and at an altitude of 9000 m. What is the absolute ceiling of this airplane?
Used Terms:
- L: Lift
- D: Drag
- Em: Maximum E(L/D)
- CD0: Zero-Lift Drag Coefficient
- K: Weight of CL^2 in Drag Polar (CD = CD0 + K*CL^2)
- c: Specific Fuel Consumption
Program Interface:
References:
[1] Bandu N. Pamadi, Performance, Stability, Dynamics, and Control of Airplanes, Second Edition, at NASA Langley Research Center, Hampton, Virginia.
[2] Maido Saarlas, Aircraft Performance, Department of Aeronautics Engineering at U.S. Naval Academy.
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