Fluid Mechanics in Channel, Pipe and Aerodynamic Design Geometries 1

Georgantopoulou, Christina G.; Georgantopoulos, G. A.

doi:10.1002/9781119457015

Cited by 1 publication

(8 citation statements)

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“…For this reason, the jet aircraft are rated in terms of thrust [38]. In both cases the aircraft's maximum velocity is defined by the curves intersection of the available and required power for the aircraft to stay in the air [18, 34].…”

Section: Uav's Technical Parameter Analysismentioning

confidence: 99%

“…The Breguet Equation (2) for a jet aircraft [34] defines that for the maximum possible range ( R ), the aircraft should fly at maximum

{\rm{C}}_{\rm{L}}^{1/2}/{{\rm{C}}}_{\rm{D}}{\rm{\ \ }}

ratio and high altitude where the specific atmospheric density is small, carry a lot of fuel and have the lowest specific fuel consumption [18].

\begin{equation}{R}_{Jet} = \frac{2}{{{{\rm{c}}}_{{\rm{th}}}}}\ \sqrt {\frac{2}{{{{{\rho}}}_{\rm{i}}{\rm{S}}}}} {\left( {\frac{{{\rm{C}}_{\rm{L}}^{\frac{1}{2}}}}{{{{\rm{C}}}_{\rm{D}}}}} \right)}_{{\rm{max}}} \cdot \left( {{\rm{w}}_0^{\frac{1}{2}} - {{\rm{w}}}_{{\rm{empty}}}^{\frac{1}{2}}} \right)\end{equation}

…”

Section: Uav's Technical Parameter Analysismentioning

confidence: 99%

“…The endurance, the amount of time that the aircraft can stay in the air on one load of fuel, has different flight conditions from the ones of maximum range mentioned previously, depending again on the aircraft's propulsion system, as depicted in Figure 2 and given below [34]:…”

Section: Uav's Technical Parameter Analysismentioning

confidence: 99%

“…The speed that the airfoil stalls, called stall speed

({V}_{stall\_i}

), depends on the air density

\ ( {{{{\rho}}}_{\rm{i}}} )

of the cruise altitude (i), the weight of the aircraft there ( w i ), and the maximum lift coefficient

\ ({C}_{{\rm{Lmax}}\_{\rm{i}}})

[34]:

\begin{equation}{V}_{stall\_i} = \sqrt {\frac{2}{{{{{\rho}}}_{\rm{i}}}}\frac{{{w}_i}}{{\rm{S}}}\frac{1}{{ \cdot {{\rm{C}}}_{{\rm{Lmax}}\_{\rm{i}}}}}} \ \end{equation}

…”

Section: Uav's Technical Parameter Analysismentioning

confidence: 99%

“…This paper focuses on the mathematical analysis of the UAV's performance, thrusted out by either a propelled engine or a jet engine, based on the analysis presented in [18, 32, 34–38]. The main purpose is to act as a guide for the calculation of the power required of any UAV type, at any flight stage.…”

Section: Introductionmentioning

confidence: 99%

See 4 more Smart Citations

A guide to unmanned aerial vehicles performance analysis—the MQ‐9 unmanned air vehicle case study

Zountouridou

Kiokes

Dimeas

et al. 2023

The Journal of Engineering

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Great efforts are devoted for integrating Renewable Energy Sources (RES) on the propulsion system of Unmanned Air Vehicles (UAVs). This is applicable to small UAVs, having a horizon to expand to large UAVs within the next decades. For the conventional propulsion systems to be replaced, the required power needs of the aircraft should first be examined. The required power depends on the UAV's flight stage from takeoff to landing, whereas its calculation varies with regard to the propulsion system type, which is separated into two main categories, the propelled-driven engines and the jet engines. Two obstacles are arising. First, the parameters needed for the power estimation are commercially sensitive and second the analysis alters with respect to the engine's type. This paper focuses on the mathematical analysis of the required power for both the main propulsion systems, presented extensively for each flight phase, proposing, at the same time, a parameter estimation method which is applicable to any UAV type. The main purpose of this paper is to act as a guide for the calculation of any type UAV's required power at any flight stage. To validate the analysis, the MQ-9 Reaper/Predator B, a High Altitude Long Endurance (HALE) turboprop UAV produced by General Atomics is analysed. Its unknown parameters are estimated and based on a selected flight profile, the required power in terms of horsepower from takeoff to landing is assessed, for two scenarios regarding the aircraft's initial weight. In the first scenario the UAV has the maximum gross takeoff weight, whereas in the second scenario it does not carry any payload. The estimated required shaft power per flight phase for each scenario is then marked into the TPE331-10 turboprop engine characteristic curves.

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Section: Uav's Technical Parameter Analysismentioning

confidence: 99%

“…The Breguet Equation (2) for a jet aircraft [34] defines that for the maximum possible range ( R ), the aircraft should fly at maximum