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CLCalculator

Categories: Aerodynamics, Flight

State: ✔️

CLCalculator determines the lift coefficient CL of an aircraft to sustain a cruise flight, for a given Mach number, altitude, and mass.

Inputs

CLCalculator only takes as input a CPACS file. The flight conditions and mass must be specified in the CPACS file.

Analyses

CLCalculator determines the Lift coefficient CL required to fly with the set of following conditions:

  • Mass of the aircraft: M [kg]
  • Mach number: Ma [-]
  • Load Factor: LF [-]
  • Reference surface area: Sref [m2]
  • Static pressure: PS [Pa]
  • Acceleration of gravity: g [m/s2]

Static pressure and acceleration of gravity can be obtained from the altitude (with the module Ambiance installed with CEASIOMpy). The reference surface area: Sref is calculated from the aircraft's geometry.

The Lift force of an aircraft is given by:

$L=\frac{1}{2}\cdot q\cdot S_{ref}\cdot C_L$

Dynamic pressure can be calculated as:

$q = \frac{1}{2} \cdot \gamma \cdot P_s \cdot M^2$

and we know the lift force must compensate for the weight of the aircraft (times the load factor), so L=M·g·LF and with the first equation, we obtain:

$C_L = \frac{M \cdot g \cdot LF}{q \cdot S_{ref}}$

Outputs

The output of CLCalculator is the target CL value to achieve, SU2 can use this value as input to make a fixed CL calculation where the angle of attack will be varied to find the correct CL.

Installation or requirements

CLCalculator is a native CEASIOMpy module, hence it is available and installed by default. To run it, you just have to be sure that you are in the CEASIOMpy Conda environment.

Limitations

When you run CLCalculator you must choose which mass it will use. However, in reality, the mass of the aircraft will vary during the flight.

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