Full‐Scale Tilt‐Rotor Hover Performance

Felker, Fort F.; Maisel, Martin D.; Betzina, Mark D.

doi:10.4050/jahs.31.2.10

Cited by 25 publications

(27 citation statements)

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“…However, force and moment measurements did not exclude the contribution from the airframe. In the mid-eighties, the most extensive data set published on the XV-15 tiltrotor in helicopter mode was realised by Felker et al (16) at the NASA-Ames Outdoor Aeronautical Research Facility (OARF). Likewise, the Boeing Vertol Company carried out rotor hover performance for the full-scale Advanced Technology Blade (ATB) and XV-15 rotor blade (17) .…”

Section: Introductionmentioning

confidence: 99%

Tiltrotor CFD Part I - validation

2017

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This paper presents performance analyses of the model-scale ERICA and TILTAERO tiltrotors and of the full-scale XV-15 rotor with high-fidelity computational fluids dynamics. For the ERICA tiltrotor, the overall effect of the blades on the fuselage was well captured, as demonstrated by analysing surface pressure measurements. However, there was no available experimental data for the blade aerodynamic loads. A comparison of computed rotor loads with experiments was instead possible for the XV-15 rotor, where CFD results predicted the FoM within 1.05%. The method was also able to capture the differences in performance between hover and propeller modes. Good agreement was also found for the TILTAERO loads. The overall agreement with the experimental data and theory for the considered cases demonstrates the capability of the present CFD method to accurately predict tiltrotor flows. In a second part of this work, the validated method is used for blade shape optimisation.

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Section: Introductionmentioning

confidence: 99%

Tiltrotor CFD Part I - validation

2017

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“…However, the rotor inflow area and the area above the model are both within interference regions of propeller inflow and wake regions. Felker, et al [6] state that the APTR is capable of supplying 2494 horsepower at 625 rpm. The rotor height was 1.76 radii from the ground to minimize ground effects on the rotor.…”

Section: Figure 21mentioning

confidence: 99%

“…It is stated that there are two paths for the thrust load to travel; through the rotor balance and through the instrumented drive shaft. Felker et al [6] indicate that the drive shaft is "compliant" in the axial direction and state that it only carried 3% of the rotor thrust. The rotor thrust balance was found to be accurate to within 11.24 lb up to 11,240 lb (0.1%) [6].…”

Section: Figure 21mentioning

confidence: 99%

“…Felker et al [6] indicate that the drive shaft is "compliant" in the axial direction and state that it only carried 3% of the rotor thrust. The rotor thrust balance was found to be accurate to within 11.24 lb up to 11,240 lb (0.1%) [6]. The instrumented driveshaft shared the same axial force accuracy when compensated for torque interaction.…”

Section: Figure 21mentioning

confidence: 99%

“…The instrumented driveshaft shared the same axial force accuracy when compensated for torque interaction. The torque measurement was accurate to within 4.8 lb•ft which was stated as less than 0.3% of the maximum torque capacity of the shaft of 1953 lb•ft [6]. Bearing torque was measured by subtracting the torque measured from the bearing torque flexures from the shaft torque.…”

Section: Figure 21mentioning

confidence: 99%

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The design of a rotor blade test facility

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Flow visualization of compressible vortex structures using density gradient techniques

Bagai

Leishman

1993

Experiments in Fluids

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Mathematical results are derived for the schlieren and shadowgraph contrast variation due to the refraction of light rays passing through two-dimensional compressible vortices with viscous cores. Both standard and small-disturbance solutions are obtained. It is shown that schlieren and shadowgraph produce substantially different contrast profiles. Further, the shadowgraph contrast variation is shown to be very sensitive to the vortex velocity profile and is also dependent on the location of the peak peripheral velocity (viscous core radius). The computed results are compared to actual contrast measurements made for rotor tip vortices using the shadowgraph flow visualization technique. The work helps to clarify the relationships between the observed contrast and the structure of vortical structures in density gradient based flow visualization experiments. Nomenclature c f Cr I 1 nb p p~ r, 0, Z rc R o0 Y F~ 7o /r p p~o 17 f2 Unobstructed height of schlieren light source in cutoff plane, m Blade chord, m Focal length of schlieren focusing mirror, m Rotor thrust coefficient, T/(pTz~2R 4) Image screen illumination, Zm/m 2 Distance from vortex to shadowgraph screen, m Number of blades Pressure, N/m 2 Ambient pressure, N/m 2 Cylindrical coordinate system Vortex core radius, m Non-dimensional radial coordinate, (r/rc) Rotor radius, m Tangential velocity, m/s Specific heat ratio of air Circulation (strength of vortex), m2/s Non-dimensional quantity, ( F 2 p~/8n2~poor 2) Refractive index of fluid medium Refractive index of fluid medium at reference conditions Gladstone-Dale constant, ma/kg Density, kg/m a Density at ambient conditions, kg/m a Non-dimensional density,

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Full‐Scale Tilt‐Rotor Hover Performance

Cited by 25 publications

References 0 publications

Tiltrotor CFD Part I - validation

Tiltrotor CFD Part I - validation

The design of a rotor blade test facility

Flow visualization of compressible vortex structures using density gradient techniques

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