NASA Aerodynamic Research Applicable to Business Aircraft

Loftin, Laurence K; Mckinney, Marion O

doi:10.4271/710378

Cited by 7 publications

(7 citation statements)

References 2 publications

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“…The method has analytical nature and uses aerodynamics and flight mechanics. It was formulated by NASA 18 and later developed by Roskam 14 and Sadraey. 12 Relationships between the required performance parameters are formulated using two new parameters, wing loading ( W/S ) and power loading ( W/P ).…”

Section: Description Of the Methodsmentioning

confidence: 99%

Optimization of small aircraft parameters in the initial phase of the project

Iwaniuk

Wiśniowski

2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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Conceptual and preliminary designs of future aircraft have become increasingly complex due to the enlargement of the basic criteria for evaluating emerging solutions. In the past, the basic performance characteristics of an airplane were the only selection criteria. Today, more and more emphasis is placed on factors such as impact on the environment, cost-effectiveness, or comfort of travel. The method for optimization of the key parameters of a small aircraft for use in the initial phase of a project is presented in this paper. It takes into account the requirements of aviation safety imposed by the European Union certification specifications CS-23 and requirements of aircraft competitiveness. Requirements and design assumptions were formulated based on the concept of the Small Air Transport system (SATs). The method is based on the multidisciplinary design optimization and covers the basic areas related to the design of aircraft: aerodynamics, aircraft structure, performance and expected operating costs. The objective function is defined as the value of the direct operating cost per passenger-kilometre. An evolutionary algorithm was applied to solve the optimization problem. As an example of the use of this method, the optimization of design parameters of the two classes of aircraft, 9-seater and 19-seater was carried out. The results were compared with the parameters of aircraft, which are in service. Sensitivity analysis of the objective function with respect to selected parameters of the aircraft was also made. The analysis allowed to select the most important parameters responsible for the operational costs.

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Section: Description Of the Methodsmentioning

confidence: 99%

Optimization of small aircraft parameters in the initial phase of the project

Iwaniuk

Wiśniowski

2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…The overall matching process, originally defined within Ref. 38 supported by Ref. 39 and subsequently subjected to updates so to be applicable to different kinds of aircraft configurations, 40 as well as specialized to meet the peculiar analyses related to high-speed vehicles, 41,42 is based on the graphical representation which relates T/W ratio to the W/S of the aircraft on a 2D chart.…”

Section: Fr@ Sosl_1000mentioning

confidence: 99%

Towards a formalized model-based process for the design of high-speed aircraft and related subsystems

Ferretto

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Increasing complexity associated to advanced aircraft concepts for high-speed flight is pushing the limit of engineering practices concerning design phases of products lifecycle. Specific methodologies aimed at managing requirements over the entire vehicle architecture definition shall then be properly formalized and supported by means of standardized processes and languages in order to be effective. The approaches suggested by the Systems Engineering practices, especially when considering the model-based environments as main tools for systems design, can be exploited to face these challenges, if properly tailored to suit the specific engineering field considered. This paper aims at proposing a model-based process for the design of high-speed aircraft exploiting a formalized methodology and the typical tools of Systems Engineering. A conceptual design exercise, based on the STRATOFLY MR3 hypersonic cruiser case study, is performed from high-level stakeholder objectives to vehicle performance estimations, passing through functional and interface analyses. Additionally, some insights concerning on-board subsystems sizing activities are provided in terms of integration within the high-level design process. The whole work highlights the capability of performing a seamless requirements management and development within the design procedure, particularly focussing on the relationships among the different stages of the workflow.

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“…The constraint diagram definition is based on formulations of Gudmundsson 49 and Loftin. 50 Within the constraint analysis script, the estimation of high-lift devices’ aerodynamics is performed using the methods of Torenbeek 51 and Roskam 52 for various types of high-lift devices. Various models to simulate the effect of altitude on the turbofan thrust are also implemented into the constraint analysis to enable more flexibility for the model calibration with respect to reference aircraft.…”

Section: Conceptual Aircraft Design Environment With Future Technolog...mentioning

confidence: 99%

Comparative study of hydrogen and kerosene commercial aircraft with advanced airframe and propulsion technologies for more sustainable aviation

Karpuk

Elham

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Present work performs a comparative study of two medium-range commercial jets with future airframe and propulsion technologies powered by hydrogen and kerosene fuel to achieve a substantial reduction in overall aviation emissions. The study aims to investigate the cumulative effect of different energy networks combined with airframe efficiency gains achieved by aircraft-related technologies to suggest a better option for the potential next-generation commercial aircraft similar to the Airbus A320. Advanced airframe and engine technologies include laminar flow control, active load alleviation, new materials and structures, and ultra-high bypass ratio turbofan engines. Two aircraft with hydrogen and kerosene propulsion systems were sized to compare their performance characteristics, equivalent CO2 emission, and direct operating costs. The design was performed using a multi-fidelity approach and included the effects of future airframe technologies and the hydrogen propulsion system. The design comparison showed a significant contribution of airframe and propulsion technologies in achieving more environmentally friendly aircraft. The green hydrogen option showed a 41–63% reduction in overall emissions compared to the kerosene aircraft depending on flight conditions while the blue hydrogen variant achieved a 21–26% reduction level. A rather optimistic price scenario shall be met to enable an operational benefit of green hydrogen while the blue hydrogen variant has more potential of being economically acceptable by the market. In circumstances when operating costs drive the decision-making more than emissions, kerosene may be a more favorable option as a compromise between emission and costs, given the positive effect of airframe and propulsion technologies.

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NASA Aerodynamic Research Applicable to Business Aircraft

Cited by 7 publications

References 2 publications

Optimization of small aircraft parameters in the initial phase of the project

Optimization of small aircraft parameters in the initial phase of the project

Towards a formalized model-based process for the design of high-speed aircraft and related subsystems

Comparative study of hydrogen and kerosene commercial aircraft with advanced airframe and propulsion technologies for more sustainable aviation

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