Conceptual Design of a Personal Aerial Vehicle Using Co-Flow Jet Airfoil

Coronado, Patricia; Cuffie, Brandon; Saer, Diego; Zha, Gecheng

doi:10.2514/6.2007-4442

Cited by 3 publications

(2 citation statements)

References 4 publications

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“…The world’s major cities are becoming increasingly overpopulated, and the land space available for ground transportation is becoming extremely limited. Therefore, air transportation may become more important in the future (Coronado et al , 2007).…”

Section: Introductionmentioning

confidence: 99%

Initial sizing of a roadable personal air vehicle using design of experiments for various engine types

Cha

Yun

Hwang

2021

AEAT

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Purpose The purpose of this paper is to analyze and compare the performances of novel roadable personal air vehicle (PAV) concepts that meet established operational requirements with different types of engines. Design/methodology/approach The vehicle configuration was devised considering the dimensions and operational restrictions of the roads, runways and parking lots in South Korea. A folding wing design was adopted for road operations and parking. The propulsion designs considered herein use gasoline, diesel and hybrid architectures for longer-range missions. The sizing point of the roadable PAV that minimizes the wing area was selected, and the rate of climb, ground roll distance, cruise speed and service ceiling requirements were met. For various engine types and mission profiles, the performances of differently sized PAVs were compared with respect to the MTOW, wing area, wing span, thrust-to-weight ratio, wing loading, power-to-weight ratio, brake horsepower and fuel efficiency. Findings Unlike automobiles, the weight penalty of the hybrid system because of the additional electrical components reduced the fuel efficiency considerably. When the four engine types were compared, matching the total engine system weight, the internal combustion (IC) engine PAVs had better fuel efficiency rates than the hybrid powered PAVs. Finally, a gasoline-powered PAV configuration was selected as the final design because it had the lowest MTOW, despite its slightly worse fuel efficiency compared to that of the diesel-powered engine. Research limitations/implications Although an electric aircraft powered only by batteries most capitalizes on the operating cost, noise and emissions benefits of electric propulsion, it also is most hampered by range limitations. Air traffic integration or any safety, and noise issues were not accounted in this study. Practical implications Aircraft sizing is a critical aspect of a system-level study because it is a prerequisite for most design and analysis activities, including those related to the internal layout as well as cost and system effectiveness analyses. The results of this study can be implemented to design a PAV. Social implications This study can contribute to the establishment of innovative PAV concepts that can alleviate today’s transportation problems. Originality/value This study compared the sizing results of PAVs with hybrid engines with those having IC engines.

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Section: Introductionmentioning

confidence: 99%

Initial sizing of a roadable personal air vehicle using design of experiments for various engine types

Cha

Yun

Hwang

2021

AEAT

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“…The CFJ airfoil has already proved to be a valuable solution for the development of high efficiency, low emission and low noise aircraft. Several futuristic high performance aircraft concepts using integrated airframe propulsion system based on CFJ airfoil are given in [24][25][26][27]. So far, all the experimental and numerical research on CFJ airfoils has used open slot injection.…”

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confidence: 99%

Experimental Study of Co-Flow Jet Airfoil Performance Enhancement Using Discreet Jets

Dano

Zha²,

Castillo

2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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This paper demonstrates a new performance enhancement methodology for Co-Flow Jet (CFJ) airfoils using discrete injection jets. This research is motivated by the hypothesis that a discrete CFJ (DCFJ) airfoil will generate both streamwise and spanwise vortex structures to achieve more effective turbulent mixing than an open slot CFJ airfoil. Aerodynamic forces and DPIV measurements show that the DCFJ airfoil can achieve up to a 250% increase of maximum lift, and simultaneously generates a tremendous thrust. Nearly 80% of the injection momentum is converted to drag reduction, which indicates that CFJ airfoils are highly energy efficient. The stall angle of attack is also significantly increased. In other words, a DCFJ airfoil is a high lift system and at the same time is also a high thrust propulsion system with low energy expenditure. Best performances are achieved with small discrete holes and large obstruction factor. Power consumption is analyzed and is found to be low compared with the performance gain. Thus, the DCFJ airfoil concept appears to be very promising for the development of integrated airframe-propulsion systems and rotorcraft systems with high performance and high efficiency. Nomenclature AoA Angle of attack C Chord length CFJ Co-flow jet CC Circulation control C L Lift coefficient C D Drag coefficient Cμ Jet momentum coefficient Cμ * Jet momentum coefficient for open slot CFJ

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Numerical and Experimental Study of the Co-Flow Jet Airfoil Performance Enhancement

Zhang

Yang

Song

et al. 2017

55th AIAA Aerospace Sciences Meeting

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Conceptual Design of a Personal Aerial Vehicle Using Co-Flow Jet Airfoil

Cited by 3 publications

References 4 publications

Initial sizing of a roadable personal air vehicle using design of experiments for various engine types

Initial sizing of a roadable personal air vehicle using design of experiments for various engine types

Experimental Study of Co-Flow Jet Airfoil Performance Enhancement Using Discreet Jets

Numerical and Experimental Study of the Co-Flow Jet Airfoil Performance Enhancement

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