Aerodynamic analysis of a helicopter fuselage with rotating rotor head

Reß, R.; Grawunder, M.; Breitsamter, C.

doi:10.1051/eucass/201507099

Cited by 5 publications

(5 citation statements)

References 1 publication

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“…Therefore, the model does not include the full main rotor and the rotor blades are truncated at about one third of the rotor radius. It is quite common in wind-tunnel measurements to use truncated rotor blades in fuselage-tail section configuration testing [10]. Therefore, using a numerical model with truncated rotor blades enables a direct comparison to experimental data.…”

Section: Modelmentioning

confidence: 99%

“…Furthermore, comprehensive experimental investigations were conducted by Le Pape et al [8] and De Gregorio [9] using active flow control in the backdoor region of a helicopter model to decrease the fuselage drag by alleviating the flow separation. In the Aerodynamic Design Optimization of a Helicopter Fuselage including a Rotating Rotor Head (ADHeRo) project [10,11], experimental and numerical investigations were performed for a Twin Engine Light (TEL) class utility helicopter providing detailed flow characteristics and drag analysis. Furthermore, the impact of passive flow control devices, like strakes and vortex generators, on the fuselage drag of a helicopter was investigated by Grawunder et al [11] and Boniface [12].…”

Section: Introductionmentioning

confidence: 99%

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Numerical Investigation of an Optimized Rotor Head Fairing for the RACER Compound Helicopter in Cruise Flight

et al. 2021

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The present work is part of the Clean Sky 2 project Full-Fairing Rotor Head Aerodynamic Design Optimization (FURADO), which deals with the aerodynamic design optimization of a full-fairing rotor head for the Rapid And Cost-Effective Rotorcraft (RACER) compound helicopter. The rotor head is a major drag source and previous investigations have revealed that the application of rotor head fairings can be an effective drag reduction measure. As part of the full-fairing concept, a new blade-sleeve fairing was aerodynamically optimized for cruise flight. Within this publication, the newly developed blade-sleeve fairing is put to test on an isolated, five-bladed rotor head and compared to an already existing reference blade-sleeve fairing, which was developed at Airbus Helicopters. Numerical flow simulations are performed with ANSYS Fluent 2019 R2 considering a rotating rotor head with cyclic pitch movement. The aerodynamic forces of the isolated rotor head are analyzed to determine the performance benefit of the newly developed blade-sleeve fairing. A drag reduction of 4.7% and a lift increase of 20% are obtained in comparison to the Airbus Helicopters reference configuration. Furthermore, selected surface and flow field quantities are presented to give an overview on the occurring flow phenomena.

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Section: Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of an Optimized Rotor Head Fairing for the RACER Compound Helicopter in Cruise Flight

et al. 2021

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“…Za stajni trap u obliku skija, postoji veliki broj rezultata dobijenih aerotunelskim i CFD istraživanjima. U pitanju su modeli trupa sa repom kome su sukcesivno dodavani različiti izvori otpora, čime je određivan doprinos svakog elementa na ukupni parazitni otpor [5], [21], [22], [27], [29], [30], [31].…”

Section: Otpor Stajnog Trapaunclassified

Single rotor helicopter parasite drag estimation in the preliminary design stage

Dodic¹,

Krstic²,

Rašuo³

2018

Tehnika

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UVODPreliminarna faza projektovanja helikoptera započinje inicijalnim dimenzionisanjem letelice na osnovu statističkih pokazatelja, da bi se tokom nje velikim brojem iterativnih ciklusa došlo do geometrijskih i aerodinamičkih karakteristika koje omogućavaju prelazak na narednu fazu, a to je detaljno projektovanje [1]. Sam postupak dimenzionisanja je istovremeno praćen primenom odgovarajuće teorije za procenu performansi, koju svaki proizvođač helikoptera razvija i unapređuje, a sve u cilju smanjenja troškova i skraći-vanja vremena potrebnog za razvoj (slika 1). Procena performansi u lebdenju ne predstavlja značajan problem, jer osnovni fizički modeli obezbeđuju solidnu tačnost sa greškom do 2%, dok je kod procene performansi prevashodno vezanih za horizontalni let, kao što su maksimalna brzina leta, maksimalni dolet, najduže trajanje leta itd., ta greška desetostruko veća, s tim da Adresa autora: Marjan Dodić, Univerzitet odbrane,

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“…Reß et al [38] studied the effect of landing gear and a rotating rotor head in a low-speed wind tunnel, which induce approximately 80% of the total parasite drag. While studying different landing gear modifications, it was found that streamlining the cross sections of the landing gear leads to 45% lower drag compared to the baseline configuration.…”

Section: Introductionmentioning

confidence: 99%

Experimental Study of Helicopter Fuselage Drag

Stepanov¹,

Zherekhov²,

Pakhov³

et al. 2016

Journal of Aircraft

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Experimental data are presented for the parasite drag of various helicopter fuselage components, such as skids, external fuel tanks, and tailplane. The experiments were conducted at the KNRTU-KAI T-1K wind tunnel, investigating four versions of a fuselage similar to the ANSAT helicopter. It was found that for the range of pitch angles −10°≤ ≤ 10°, the skids added 80% to the drag of the bare fuselage, while the tailplane increased the drag by 20%. At the same conditions, external fuel tanks were found to add 48% to the clean fuselage drag. A simple rotor hub with a tail support added 74% to the bare fuselage in the range of pitch angles −8°≤ ≤ 6°. Streamlining the rear fuselage was found to reduce the drag by 16% over the range of pitch angles −10°≤ ≤ 10°. Apart from the parasite drag, ideas for drag reduction are also discussed. Nomenclature

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Aerodynamic analysis of a helicopter fuselage with rotating rotor head

Cited by 5 publications

References 1 publication

Numerical Investigation of an Optimized Rotor Head Fairing for the RACER Compound Helicopter in Cruise Flight

Numerical Investigation of an Optimized Rotor Head Fairing for the RACER Compound Helicopter in Cruise Flight

Single rotor helicopter parasite drag estimation in the preliminary design stage

Experimental Study of Helicopter Fuselage Drag

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