. Methodology for calculating the flight range of a bomb equipped with wings
DOI:
https://doi.org/10.34169/2414-0651.2025.1(45).39-44Keywords:
aerial bomb, bomb gliding, flight trajectory, aerodynamic efficiency, flight range, turbojet engineAbstract
The article presents a methodology for calculating the maximum flight range of a bomb equipped with wings and a turbojet engine. Working formulas are derived for calculating the bomb's flight range, taking into account the improvement of its aerodynamic efficiency due to the addition of a gliding module and the installation of a cruise engine.
A methodology is proposed for determining the main aerodynamic characteristics of a gliding bomb and constructing its polar diagram based on the results of a flight experiment with a model. An assessment is made of the impact of engine thrust on the bomb's flight range. It is shown that installing an engine reduces the gliding trajectory angle of the bomb by a value proportional to the ratio of thrust to the bomb’s weight. Calculation dependencies are proposed to determine the optimal moment for starting the cruise engine after the bomb is released from the carrier.
Using the energy method, it is proven that the lowest fuel consumption for obtaining the same thrust impulse is achieved when the engine is started at the initial phase of the flight, while the bomb's gliding for maximum range should be performed at the most advantageous indicated airspeed. The conditions for achieving the maximum flight range of the bomb are determined. Calculation dependencies are provided for determining the maximum range, taking into account all phases of the bomb’s flight.
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Copyright (c) 2025 Валерій Сілков ,Михайло Мітрахович ,Андрій Зірка
This work is licensed under a Creative Commons Attribution 4.0 International License.
