For a jet aeroplane, at what speed is the maximum climb angle generally achieved?

The maximum climb angle for a jet aeroplane is attained at the speed that corresponds to the maximum lift-to-drag ratio (CL/CD ratio). This is fundamental in aerodynamics as it indicates the most efficient flight configuration for gaining altitude. At this speed, the aircraft is able to generate the most lift for the least amount of drag, thereby maximizing its performance during the climb phase.

When the aircraft is flown at the speed that provides this optimal CL/CD ratio, it means that it can achieve the greatest height for the horizontal distance it travels. This is especially crucial during climb segments where every foot of altitude gained is tied closely to the aircraft's climb performance and fuel efficiency.

While other speeds such as 1.37 VS or 1.32 VMD may refer to different aspects of aircraft performance, the critical point here is that the maximum CL/CD ratio directly links to achieving the steepest climb angle, which is essential for operational efficiency in climb profiles of jet aeroplanes.