Calculating Cruise Flight Performance of Jet-Engine Aircrafts V2.0

by admin in , , on April 23, 2019

This 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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