What occurs to the climb angle and pitch angle when a jet aeroplane climbs at a constant IAS with maximum climb thrust?

When a jet aeroplane climbs at a constant Indicated Airspeed (IAS) with maximum climb thrust, the climb angle and pitch angle are both influenced by the relationship between thrust and drag, along with the aircraft's weight and aerodynamic characteristics.

As the aircraft climbs under maximum thrust, it generates the highest vertical speed possible while maintaining a constant speed through the air. However, maintaining a constant IAS means that as the altitude increases, the air density decreases, which affects the lift generated by the wings. To compensate for this reduction in lift due to lower air density, the pitch angle needs to be adjusted.

To maintain a constant IAS during the climb, pilots often have to lower the pitch angle slightly to prevent the aircraft from unintentionally accelerating. This adjustment allows the aircraft to manage drag effectively, as an increase in pitch would typically result in a decrease in airspeed unless additional thrust is provided. As a result, both the climb angle and pitch angle will reduce during this phase, as the aircraft balances maintaining the set speed with the maximum climb performance.

Hence, saying the climb angle and pitch angle reduce during this constant climb at maximum thrust is accurate, reflecting the need for adjustments in the aircraft’s attitude to maintain both speed and optimal climb rate.