Development and validation of an enhanced semi-empirical method for estimation of aerodynamic characteristics of light, propeller-driven airplanes

Rostami, Mohsen; Bagherzadeh, Seyed Amin

doi:10.1177/0954410016683415

Cited by 8 publications

(11 citation statements)

References 9 publications

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“…This research builds on previous work in which an enhanced semi-empirical method, called NAMAYEH, was developed to calculate longitudinal and lateraldirectional stability and control derivatives of light airplanes. [17][18][19][20][21][22][23][24] In this study, an engineering method is provided to perform vertical tail sizing considering stability and control including the asymmetrical blade thrust effects. A case study was developed considering a twinengined aircraft equipped with propellers rotating in the clockwise direction with respect to the pilot's field of view.…”

Section: Critical Enginementioning

confidence: 99%

“…Recently, several studies have enhanced semiempirical methods to investigate the aerodynamic characteristics of more sophisticated propeller-driven airplanes and the propeller effects on the handling quality. [18][19][20][21][22][23][24] These studies attempted to modify and combine stateof-the-art analytical procedures and design data compendia in compatible methods to compensate for the limitations of the previous methods.…”

Section: Introductionmentioning

confidence: 99%

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Vertical tail sizing of propeller-driven aircraft considering the asymmetric blade effect

Rostami

Chung

Neufeld

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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An engineering approach is presented to analyse the asymmetric blade thrust effect with the help of analytical and semi-empirical methods. It is shown that the contribution of the asymmetric blade thrust effect in the lateral-directional stability of multi-engine propeller-driven aircraft is significant particularly in critical flight conditions with one engine out of service. Also, in some cases where the engines are rotating in one direction, the asymmetric blade effect has substantial effects on the handling qualities of the aircraft even in normal flight conditions. Overall, due to the significant contribution of this phenomenon in the lateral-directional stability of propeller-driven airplanes, it is important to consider it in the design of the vertical stabilizer and rudder. The resulting analytical method has been used to determine the vertical tail incident angle and desired rudder deflection in accordance with the most critical flight condition for two different cases and validated to ensure the accuracy of the result. In this work, the aerodynamic coefficients as well as the stability and control derivatives have been predicted using analytical and semi-empirical methods validated for light aircraft.

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Section: Critical Enginementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Vertical tail sizing of propeller-driven aircraft considering the asymmetric blade effect

Rostami

Chung

Neufeld

2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…It should also be noted that each component of this system works independently of the others. 10 In order to introduce each term, one can assume that the rest of the terms are zero. Therefore, assuming K i ¼ K d ¼ 0; uðtÞ is equal to K p e ðtÞ.…”

Section: Pid Controllermentioning

confidence: 99%

“…As discussed earlier in the introduction, herein the aerodynamic characteristics of the airplane have been estimated through NAMAYEH. 10 The investigated airplane is a six-place, low wing, twin-engine, propeller-driven general aviation airplane. General characteristics of the airplane are presented in Table 1.…”

Section: Flying Qualitymentioning

confidence: 99%

“…8,9 Recently, several studies have been done to enhance semi-empirical methods to investigate aerodynamic characteristics of propeller-driven airplanes and their effects on the handling quality. [10][11][12][13][14][15] Generally, in single-engine light propeller-driven airplanes, in order to decrease the asymmetrical propeller thrust, one can use a small side angle (i.e. typically to the right-hand side for a clockwise rotating propeller from a pilot field of view).…”

Section: Introductionmentioning

confidence: 99%

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Design optimization of multi-objective proportional–integral–derivative controllers for enhanced handling quality of a twin-engine, propeller-driven airplane

Rostami

Chung

Park

2020

Advances in Mechanical Engineering

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Herein, the design optimization of multi-objective controllers for the lateral–directional motion using proportional–integral–derivative controllers for a twin-engine, propeller-driven airplane is presented. The design optimization has been accomplished using the genetic algorithm and the main goal was to enhance the handling quality of the aircraft. The proportional–integral–derivative controllers have been designed such that not only the stability of the lateral–directional motion was satisfied but also the optimum result in longitudinal trim condition was achieved through genetic algorithm. Using genetic algorithm optimization, the handling quality was improved and placed in level 1 from level 2 for the proposed aircraft. A comprehensive sensitivity analysis to different velocities, altitudes and centre of mass positions is presented. Also, the performance of the genetic algorithm has been compared to the case where the particle swarm optimization tool is implemented. In this work, the aerodynamic coefficients as well as the stability and control derivatives were predicted using analytical and semi-empirical methods validated for this type of aircraft.

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Conceptual design and analysis of a box fan-in-split-wing tiltrotor eVTOL aircraft

Oyama,

Rostami,

Chung

2024

AEAT

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Purpose With the advancements in electric vertical take-off and landing (eVTOL) aircraft technology such as batteries, mechanisms, motors, configurations and so on, designers and engineers are encouraged to create unique and unconventional configurations of eVTOL aircraft to provide better capabilities and higher efficiencies to compete in the market. The box fan-in-split-wing tiltrotor eVTOL aircraft is an innovative design that aims to address the aerodynamic inefficiencies such as propeller effects in cruise and engine mounts drag that existed in traditional eVTOL aircraft designs such as vectored thrust, rotorcraft, lift + cruise and multi-copter configurations. This paper aims to propose a multi-disciplinary design process to conceptually design the box fan-in-split-wing Tiltrotor eVTOL aircraft. Design/methodology/approach An unconventional methodology was used to design the UAM aircraft, and the following parameters are considered: capable of vertical take-off and landing, highly aerodynamic with a high lift-to-drag ratio, low Cd0 modern and appealing, rechargeable or battery swappable and feature to minimise or negate propeller drag. A heavy emphasis on improving performance and weight based on aerodynamics was enforced during the conceptual design phase. MAPLA and XFOIL were used to identify the aerodynamic properties of the aircraft. Findings Upon determining the key parameters and the mission requirements and objectives, a list of possible VTOL configurations was derived from theoretical and existing designs. The fan in the wing/split wing was selected, as it could stow the propellers. A tiltrotor configuration was selected because of its ability to reduce the total number of lift props/motors, reducing powerplant weight and improving aerodynamic efficiency. For the propulsion configuration, a battery–motor configuration with a hexa-rotor layout was chosen because of its ability to complement the planform of the aircraft, providing redundant motors in case of failure and because of its reliability, efficiency and lack of emissions. Coupled with the fan-in-wing / split wing concept, the box wing seamlessly combines all chosen configurations. Originality/value The box fan-in-split-wing Tiltrotor eVTOL aircraft aims to address the aerodynamic inefficiencies of earlier designs such as propeller effects in cruise and engine mounts drag. The potential benefits of this aircraft, such as increased range, endurance and payload capacity, make it an exciting prospect in the field of Urban Air Mobility.

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Development and validation of an enhanced semi-empirical method for estimation of aerodynamic characteristics of light, propeller-driven airplanes

Cited by 8 publications

References 9 publications

Vertical tail sizing of propeller-driven aircraft considering the asymmetric blade effect

Vertical tail sizing of propeller-driven aircraft considering the asymmetric blade effect

Design optimization of multi-objective proportional–integral–derivative controllers for enhanced handling quality of a twin-engine, propeller-driven airplane

Conceptual design and analysis of a box fan-in-split-wing tiltrotor eVTOL aircraft

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