Performance and Vibratory Loads Data from a Wind-Tunnel Test of a Model Helicopter Main-Rotor Blade with a Paddle-Type Tip

Yeager, Jr William T.; Kevin, W Noonan; Jeffrey, D Singleton; Matthew, L Wilbur; Paul, Hanna

doi:10.21236/ada406400

Cited by 5 publications

(20 citation statements)

References 4 publications

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“…The geometric properties of the four rotor blades considered within this paper are described here: the Langley Baseline (LBL) and Langley BERP blades (LBERP) [43], PSP rotor [42], and the XV-15 tiltrotor blade [44].…”

Section: Blade Geometriesmentioning

confidence: 99%

“…The main aim of the selected computations is to cover a variety of collectives, tip Mach numbers and blade geometries. Further information on the exact experimental conditions can be found in the respective references for each rotor blade design: XV-15 [44], PSP [12,42], Langley Baseline (LBL) and Langley BERP (LBERP) [43].…”

Section: Computational Setup and Test Conditionsmentioning

confidence: 99%

“…There is little experimental data for advanced planform validation. To our knowledge, the only experimental data set available is the wind tunnel test performed by Yeager et al [43] for a blade with a paddle-like tip shape along with a standard rectangular blade. This dataset is used within this paper to validate the method for more advanced blade planforms as well as comparison with a conventional rotor design.…”

Section: Introductionmentioning

confidence: 99%

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Validation of the Steady-State Hover Formulation for Accurate Performance Predictions

et al. 2019

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This paper shows accurate predictions for hover performance regardless of planform geometry, blade tip Mach number or disk loading. To prove this statement, sensitivity analyses were performed along with performance predictions for four rotor designs. Planform effects were also studied, such as blade anhedral, showing the strong sensitivity of the rotor blade performance due to geometric features. The steady state solution methodology with imposed Froude boundary conditions is shown to give accurate results for relatively coarse grid sizes. This approach leads to reduced computational costs compared to time-dependent simulations. It is also recognised that given the current accuracy of the available experimental data, the use of more advanced CFD methods may not be fully justified. To advance the accuracy of modern CFD methods a more comprehensive experimental dataset is required. Nomenclature AR = aspect ratio, R/c r e f a = speed of sound, m/s C p = pressure coefficient, (p − p ∞ )/(1/2ρ(Ωr/R) 2 ) C f = skin friction coefficient, τ w /(1/2ρ(Ωr/R) 2 ) C Q = torque coefficient, Q/( ρ(ΩR) 2 πR 3 ) C T = thrust coefficient, T/( ρ(ΩR) 2 πR 2 ) c = rotor chord, m E = endurance, s FoM = figure of merit, C 3/2 T /( √ 2C Q ) k = turbulent kinetic energy, m 2 /s 2 M = Mach number, V ∞ /a ∞ M tip = blade tip Mach number, ΩR/a ∞ * PhD Student, CFD Laboratory, School of Engineering.

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Section: Blade Geometriesmentioning

confidence: 99%

Section: Computational Setup and Test Conditionsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Validation of the Steady-State Hover Formulation for Accurate Performance Predictions

et al. 2019

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“…1 are the subject of this study: the Langley Baseline blade (LBL) with a rectangular planform, the Langley BERP blade (LBERP) with a paddle-shaped tip and the PSP blade with a swept-tapered blade tip and a scaled Langley Baseline blade (LBLs) to examine solidity effects. The LBERP and LBL blades were tested by Yeager et al (6) at model scale in a Freon-12 medium with a higher density than air. This allowed tests closer to full scale Reynolds numbers.…”

Section: Blade Geometriesmentioning

confidence: 99%

“…Despite the findings of Perry (5) , the thrust-weighted solidity parameter (or equivalent rectangular blade), continues to be used in many rotor design studies found in literature. The experiments by Yeager et al (6) , matched the thrust-weighted solidity between a rectangular and BERP planform. Various optimisation studies have also kept this parameter constant (7)(8)(9) , which leads to favourable treatment of planforms with lower blade area across the blade tip, as seen by Perry (5) for the BERP and tapered planforms.…”

Section: Introductionmentioning

confidence: 99%

Assessment of current rotor design comparison practices based on high-fidelity CFD methods

2020

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This paper provides an assessment of current rotor design comparison practices. First, the employed CFD method is validated for a number of rotor designs and is shown to achieve accurate performance predictions in hover and high-speed forward flight. Based on CFD results, a detailed investigation is performed in terms of comparing different rotor designs. The CFD analysis highlighted the need of high fidelity methods due to the subtle aerodynamics involved in advanced planforms. Nevertheless, the paper suggests that the correct basis for comparison in terms of performance metrics must be used to inform decisions about the suitability of the rotor blades designs for specific applications. In particular, when comparing blades of advanced planforms, direct torque and thrust comparisons are better than the commonly used lift to drag ratio and figure of merit.

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Design of a rotor blade tip for the investigation of dynamic stall in the transonic wind-tunnel Göttingen

Lütke¹,

Nuhn²,

Govers³

et al. 2016

Aeronaut. j.

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The aerodynamic and structural design of a pitching blade tip with a double-swept planform is presented. The authors demonstrate how high-fidelity finite element (FE) and computational fluid dynamic (CFD) simulations are successfully used in the design phase. Eigenfrequencies, deformation, and stress distributions are evaluated by means of a three-dimensional (3D) FE model. Unsteady Reynolds-averaged Navier-Stokes (RANS) simulations are compared to experimental data for a light dynamic stall case atMa= 0.5,Re= 1.2 × 106. The results show a very good agreement as long as the flow stays attached. Tendencies for the span-wise location of separation are captured. As soon as separation sets in, discrepancies between experimental and numerical data are observed. The experimental data show that for light dynamic stall cases atMa= 0.5, a factor of safety ofFoS= 2.0 is sufficient if the presented simulation methods are used.

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Performance and Vibratory Loads Data from a Wind-Tunnel Test of a Model Helicopter Main-Rotor Blade with a Paddle-Type Tip

Abstract: Summary

Cited by 5 publications

References 4 publications

Validation of the Steady-State Hover Formulation for Accurate Performance Predictions

Validation of the Steady-State Hover Formulation for Accurate Performance Predictions

Assessment of current rotor design comparison practices based on high-fidelity CFD methods

Design of a rotor blade tip for the investigation of dynamic stall in the transonic wind-tunnel Göttingen

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