Aircraft Performance Question -- Berguet

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SUMMARY

The discussion focuses on determining the optimal cruise velocity for an aircraft to maximize its cruise range using the Breguet Equation. Key parameters include an aircraft mass of 14,000 kg, a fuel mass of 2,500 kg, a specific fuel consumption (sfc) of 2.8×10-5 kg/N/s, and a drag polar defined as CD = 0.02 + 0.08CL2. The coefficient of lift (Cl) is derived from the lift equation, which states Cl = 2L/(ρV2S), where L is the lift force, ρ is air density, V is velocity, and S is the wing area of 65 m2.

PREREQUISITES
  • Understanding of the Breguet Equation for aircraft performance
  • Knowledge of lift and drag equations in aerodynamics
  • Familiarity with specific fuel consumption (sfc) calculations
  • Basic principles of flight dynamics and equilibrium
NEXT STEPS
  • Study the Breguet Equation in detail to understand its application in range optimization
  • Learn how to calculate the coefficient of lift (Cl) using various flight conditions
  • Explore the relationship between drag polar and aircraft performance
  • Investigate the effects of varying fuel mass on cruise range and velocity
USEFUL FOR

Aerospace engineers, flight performance analysts, and students studying aircraft design and performance optimization will benefit from this discussion.

LaReina
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Homework Statement


What cruise velocity should the aircraft fly to maximize the cruise range?
Aircraft mass (excluding fuel), m0= 14000kg
Mass of fuel, mf = 2500kg
Specific fuel consumption of aircraft engine, sfc = 2.8\times10-5 kg/N/s
Drag polar, CD = 0.02+0.08CL^2
Planform area of aircraft wings, S = 65m2

Homework Equations


Breguet Equation
Coefficient of Lift

The Attempt at a Solution


I am trying to find the coefficient of lift but there has been no given velocity. I then try to find the velocity but there is no given coefficient of lift. I feel like I'm going around in circles.
Cl=2L/ρV2S
L=W (14000+2500)\times9.81=161865N
 
Last edited:
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Are you not assuming uniform level flight?
Does that not make the lift equation rather simple?

How about showing the details of the working, with reasoning, that you have already.
 

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