Hello,
I wonder what the maximum L/D (or even better the maximum performance glide polar) of a rotorcraft in autorotation can be based on the following assumption:
No drag from the pod
No drag from mechanical parts
known profile drag of the blade sections
known parasitic drag (blades probably operating in fully turbulent conditions)
known induced drag of blades (I assume the lift distribution to be horrible).
How can the L/D polar (or even the speed for vertical descent at a given weight) be derived from these assumptions?
cheers,
y
I wonder what the maximum L/D (or even better the maximum performance glide polar) of a rotorcraft in autorotation can be based on the following assumption:
No drag from the pod
No drag from mechanical parts
known profile drag of the blade sections
known parasitic drag (blades probably operating in fully turbulent conditions)
known induced drag of blades (I assume the lift distribution to be horrible).
How can the L/D polar (or even the speed for vertical descent at a given weight) be derived from these assumptions?
cheers,
y
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