Validation of a Flow Simulation for a Helicopter Fuselage Including a Rotating Rotor Head

Grawunder, M.; Reß, R.; Stein, Victor; Breitsamter, Christian; Adams, Nikolaus A.

doi:10.1007/978-3-319-27279-5_27

Cited by 7 publications

(10 citation statements)

References 2 publications

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“…Parasite drag reduction has become increasingly important during the last decade because of the potentially significant gains it may bring to the aerodynamic performance and the minimization of fuel consumption [7][8][9]. Parasite drag is the aggregate drag of parts of a helicopter (e.g., tailplane, skids, rotor head etc.…”

Section: Introductionmentioning

confidence: 99%

“…Grawunder et al [7] carried out WT experiments and numerical computations on a similar type TEL-class helicopter, where the case with rotating rotor head, trimmed for fast level flight was investigated. Drag values for this model were slightly higher because the tailboom was truncated upstream of the stabilizer to fit the balance support.…”

Section: Introductionmentioning

confidence: 99%

“…Level cruise flight, Wagner [12] WT experiment, Grawunder [7] CFD, Grawunder [7] -∝= 0°, = 0° ∝= 0°, = 0° Table 1. Parasite drag breakdown in percentage of total parasite drag for a typical TEL-class utility helicopters (with no external fuel tanks) [7] According to Stroub and Rabbot [19], the total consumed power for a typical TEL helicopter in forward flight consists of the parasite power, induced power, profile power and tail rotor power.…”

Section: Introductionmentioning

confidence: 99%

“…Parasite drag breakdown in percentage of total parasite drag for a typical TEL-class utility helicopters (with no external fuel tanks) [7] According to Stroub and Rabbot [19], the total consumed power for a typical TEL helicopter in forward flight consists of the parasite power, induced power, profile power and tail rotor power. The parasite power makes up about 50 % of total power requirement.…”

Section: Introductionmentioning

confidence: 99%

“…The parasite power makes up about 50 % of total power requirement. The parasite power can be estimated as follows [7]:…”

Section: Introductionmentioning

confidence: 99%

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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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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

“…The parasite power makes up about 50 % of total power requirement. The parasite power can be estimated as follows [7]:…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Experimental Study of Helicopter Fuselage Drag

Stepanov¹,

Zherekhov²,

Pakhov³

et al. 2016

Journal of Aircraft

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Wind Tunnel Analysis of Helicopter Aerodynamics with Varying Rotor Head Blade Stub Lengths

Hartmann,

Ruhland,

Breitsamter

2023

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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Aerodynamic characteristics of helicopter engine side air intakes

Knoth

Breitsamter

2018

AEAT

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PurposeAerodynamic characteristics of engine side air intakes for a lightweight helicopter are investigated aiming to achieve an efficient engine airframe integration. Design/methodology/approachOn a novel full-scale model of a helicopter fuselage section, a comprehensive experimental data set is obtained by wind tunnel testing. Different plenum chamber types along with static side intake and semi-dynamic side intake configurations are considered. Engine mass flow rates corresponding to the power requirements of realistic helicopter operating conditions are reproduced. For a variety of freestream velocities and mass flow rates, five-hole pressure probe data in the aerodynamic interface plane and local surface pressure distributions are compared for the geometries. FindingsIn low-speed conditions, unshielded, sideways facing air intakes yield lowest distortion levels and total pressure losses. In fast forward flight condition, a forward-facing intake shape is most beneficial. Additionally, the influence of an intake grid and plenum chamber splitter is evaluated. Originality/valueThe intake testing approach and the trends found can be applied to other novel helicopter intakes in early development stages to improve engine airframe integration and decrease development times.

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Validation of a Flow Simulation for a Helicopter Fuselage Including a Rotating Rotor Head

Cited by 7 publications

References 2 publications

Experimental Study of Helicopter Fuselage Drag

Experimental Study of Helicopter Fuselage Drag

Wind Tunnel Analysis of Helicopter Aerodynamics with Varying Rotor Head Blade Stub Lengths

Aerodynamic characteristics of helicopter engine side air intakes

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