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Figure 6 Deorbit analysis for a 10 kg 6U CubeSat in minimum drag configuration.
In order to demonstrate the potential de-orbit period of a 10 kg 6U CubeSat, it is assumed that the CubeSat would be in minimum drag configuration (i.e. minimum projected area) and that the CubeSat would be launched from the ISS in Q1 of 2018.
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The method is then used in a range of optimisation problems covering the design of a coastal defence, increasing fluid damping within an oscillating box by the addition of baffles, and design of a multi-body configuration for minimum drag in supersonic flow.
A shape optimization problem concerned with minimum drag of a thin wing is considered.
"To pass a car, you need to know precisely where the minimum drag is for you and the maximum drag is for him.
minimum drag coefficient, at α = A0, for all aspect ratios.
The optimization target is to obtain the minimum drag coefficient.
The optimization is carried out for maximum lift and minimum drag.
New necessary conditions for minimum drag are obtained which are stronger than the Legendre condition.
A strong correspondence to the minimum drag coefficient is also observed.
This paper describes a new technology of aerodynamic design based on CFD driven constrained optimization to minimum drag.
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