Selected results from the quiet short-haul research aircraft flight research program

Cochrane, John H.; Riddle, D. W.; Stevens, Victor C.; Shovlin, M. D.

doi:10.2514/3.44814

Cited by 7 publications

(4 citation statements)

References 3 publications

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“…For example, Posey et al [70] leveraged a DP system on a twin-fuselage platform and projected a low-frequency (f ≤ 320 Hz) reduction in noise of 20 dB across large community areas. A similar noise shielding approach was utilized in the development of the Quiet Short-Haul Research Aircraft vehicle developed by NASA [71][72][73][74][75]. Flight-test results from this research aircraft campaign demonstrated noise levels of 90 EPNdB as measured at a sideline of 500 ft, which for the time was considerably lower than comparable jet transport aircraft [72].…”

Section: Distributed Electric Propulsion Enabled Noise Reductionmentioning

confidence: 99%

A Review of Distributed Electric Propulsion Concepts for Air Vehicle Technology

Kim

Perry

Ansell

2018

2018 AIAA/IEEE Electric Aircraft Technologies Symposium

229

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The emergence of distributed electric propulsion (DEP) concepts for aircraft systems has enabled new capabilities in the overall efficiency, capabilities, and robustness of future air vehicles. Distributed electric propulsion systems feature the novel approach of utilizing electrically-driven propulsors which are only connected electrically to energy sources or power-generating devices. As a result, propulsors can be placed, sized, and operated with greater flexibility to leverage the synergistic benefits of aero-propulsive coupling and provide improved performance over more traditional designs. A number of conventional aircraft concepts that utilize distributed electric propulsion have been developed, along with various short and vertical takeoff and landing platforms. Careful integration of electrically-driven propulsors for boundary-layer ingestion can allow for improved propulsive efficiency and wake-filling benefits. The placement and configuration of propulsors can also be used to mitigate the trailing vortex system of a lifting surface or leverage increases in dynamic pressure across blown surfaces for increased lift performance. Additionally, the thrust stream of distributed electric propulsors can be utilized to enable new capabilities in vehicle control, including reducing requirements for traditional control surfaces and increasing tolerance of the vehicle control system to engine-out or propulsor-out scenarios. If one or more turboelectric generators and multiple electric fans are used, the increased effective bypass ratio of the whole propulsion system can also enable lower community noise during takeoff and landing segments of flight and higher propulsive efficiency at all conditions. Furthermore, the small propulsors of a DEP system can be installed to leverage an acoustic shielding effect by the airframe, which can further reduce noise signatures. The rapid growth in flight-weight electrical systems and power architectures has provided new enabling technologies for future DEP concepts, which provide flexible operational capabilities far beyond those of current systems. While a number of integration challenges exist, DEP is a disruptive concept that can lead to unprecedented improvements in future aircraft designs.

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Section: Distributed Electric Propulsion Enabled Noise Reductionmentioning

confidence: 99%

A Review of Distributed Electric Propulsion Concepts for Air Vehicle Technology

Kim

Perry

Ansell

2018

2018 AIAA/IEEE Electric Aircraft Technologies Symposium

229

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“…To validate the calculations for the blown flaps, the results were compared to data from the QSRA. Flight test data from the QSRA [9,10,30,31] were used to compare the lift coefficients achieved by the QSRA and those computed for the Cardinal. Maximum lift coefficients for the Cardinal were 4-5 in the takeoff configuration and 10-12 in the landing configuration.…”

Section: High Lift and Powered Lift Designmentioning

confidence: 99%

1998/1999 AIAA Foundation Graduate Team Aircraft Design Competition: Super STOL Carrier On-board Delivery Aircraft

LeGresley

Bathke

Carrion

et al. 2000

SAE Technical Paper Series

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The Cardinal is a Super Short Takeoff and Landing (SSTOL) aircraft, which is designed to fulfill the desire for center-city to center-city travel by utilizing river "barges" for short takeoffs and landings to avoid construction of new runways or heliports. In addition, the Cardinal will fulfill the needs of the U.S. Navy for a Carrier On-board Delivery (COD) aircraft to replace the C -2 Greyhound. Design requirements for the Cardinal included a takeoff ground roll of 300 ft, a landing ground roll of 400 ft, cruise at 350 knots with a range of up to 1500 nm with reserves, payload of 24 passengers and baggage for a commercial version or a military version with a 10,000 lb payload, capable of carrying two GE F110 engines for the F-14D, and a spot factor requirement of 60 feet by 29 feet.

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“…Additionally, the lift augmentation systems influence the flow conditions downstream of the wing in the region of the tail plane. Investigations of similar aircraft configurations suggest that the aircraft's stability can be negatively affected [5], even though the impact is rarely documented [6], [7], [8]. In particular, detailed information about the origin of the change in the stability behavior is lacking due to the experimental character of these investigations.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigations of aerodynamic properties of a propeller blown circulation control system on a high wing aircraft

Keller

Rudnik

2016

CEAS Aeronaut J

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The contribution gives an overview over a wide range of CFD simulations, which were performed in the course of the German collaborative research center 880 in order to investigate the aerodynamic properties of a complete turboprop powered transport aircraft in landing configuration with a circulation control high-lift system. The main purpose of the contribution is to highlight aerodynamic and flight mechanical aspects of the integration of lift augmentation technologies into the design of a short takeoff and landing aircraft concept. In this context, the influence of engine nacelles and thrust on the stall behavior and the following improvements due to the use of a nacelle strake are discussed. Furthermore, static longitudinal and lateral stability as well as the dynamic longitudinal stability are investigated. While circulation control itself has a rather small impact on the stability, the impact of engine thrust in conjunction with circulation control is considerable. Additionally, the one engine inoperative case was simulated. For some flow and engine conditions, the resulting yawing moments are more than twice as high as the actual yawing moments due to asymmetric thrust.

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Selected results from the quiet short-haul research aircraft flight research program

Cited by 7 publications

References 3 publications

A Review of Distributed Electric Propulsion Concepts for Air Vehicle Technology

A Review of Distributed Electric Propulsion Concepts for Air Vehicle Technology

1998/1999 AIAA Foundation Graduate Team Aircraft Design Competition: Super STOL Carrier On-board Delivery Aircraft

Numerical investigations of aerodynamic properties of a propeller blown circulation control system on a high wing aircraft

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