Propeller/wing interaction

Witkowski, David; Johnston, Robert; Sullivan, John P.

doi:10.2514/6.1989-535

Cited by 13 publications

(5 citation statements)

References 5 publications

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“…Fundamental descriptions of the aerodynamic interactions that dominate the PWF system and, in particular, how these differ from related sub-fields like propeller-wing interaction and multi-element aerodynamics, are still lacking in literature for PWF systems. Notable literature on propeller-wing interaction [12][13][14] focus mostly on cruise conditions and single-element wings, and while some literature on propeller slipstream development in the presence of a wing does include the high-lift condition [15,16], there is little attention for the interaction with the flap as a separate element in the system.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation of Aerodynamic Interactions of a Wing with Deployed Fowler Flap under Influence of a Propeller Slipstream

Duivenvoorden

Suard

Sinnige

et al. 2022

AIAA AVIATION 2022 Forum

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Experiments were performed using a wall-to-wall unswept and untapered wing with a single slotted flap and a propeller, to obtain a validation dataset and gain insight into primary flow phenomena in propeller-wing-flap interactions. Measurements were taken using pressure taps, a wake rake and oil flow visualization, for several flap deflections (0, 15 and 30 degrees) and thrust settings (unpowered, 𝐽 = 0.8 / 𝑇 𝑐 = 1.05 and 𝐽 = 1.0 / 𝑇 𝑐 = 0.45). Similarity of the measured data to similar experiments was poor, which was believed to be due to the low Reynolds number of 𝑅𝑒 = 6𝑒5 and sensitivity of local measurements due to occurrence of stall cells. Oil flow visualizations showed significant induction of flow separation from nacelle-wing interactions in unpowered conditions, traced to boundary layer growth. For powered cases it was shown that both sides of the deployed flap are immersed in the part of the slipstream that passes the pressure side of the main element. This part of the slipstream deforms significantly before it reaches the flap and thus results in complex spanwise variations for the flap flow. This stresses the need to investigate slipstream development in propeller-wing-flap systems and the effects on flap flow specifically to gain in-depth understanding of the interactions. The results presented in this paper expose the inherent complexity of investigating propeller-wing-flap systems and gaining viable validation data, and might serve to guide for future investigations of propeller-wing-flap systems.

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Section: Introductionmentioning

confidence: 99%

Experimental Investigation of Aerodynamic Interactions of a Wing with Deployed Fowler Flap under Influence of a Propeller Slipstream

Duivenvoorden

Suard

Sinnige

et al. 2022

AIAA AVIATION 2022 Forum

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“…His wind tunnel tests allowed to observe propeller influence effects on a trailing wing, as well as wing induced effects on a tractor propeller [8]. Later in the 1980's, works by Kroo [9], Miranda [10] and Witkowski [11] shed light on the aerodynamic performance improvement opportunities of a well integrated system. Recently Veldhuis and Heyma [12], and Ferraro et al [13] developed methodologies to estimate wing-propeller interaction effects, and the formers attempted the exploitation of such interaction by performing an aerodynamic optimization on a wing-propeller system.…”

Section: Nomenclature Latin Symbolsmentioning

confidence: 99%

“…Witkowski [11] performed an investigation of the mentioned phenomenon, providing both theoretical and experimental proof of what he called hub lift (here referred to as propeller normal force). The perturbation on the propeller inflow modifies its performance and the pattern of induced velocities which the wing eventually sees.…”

Section: Wing Induced Up-washmentioning

confidence: 99%

A Surrogate-Based Multi-Disciplinary Design Optimization Framework Exploiting Wing-Propeller Interaction

Alba

Elham

German

et al. 2017

18th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference

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The adoption of propellers is the oldest propulsive solution in aviation, and remains nowadays the preferred one in several segments of the market, being the greenest and most fuel-efficient choice for low-to-mid subsonic speeds. New paradigms of mobility envision the use of propeller powered aircrafts to provide an answer to the issue of future mass transportation in and between major cities.Common aircraft design procedures determine optimal wing design parameters pursuing low drag and weight solutions, but neglecting the influence that propellers' slipstreams have on lift and drag distributions, especially when mounted in tractor configurations.Considering such strong interest in propeller propulsion, and the apparent lack of insightful research in the multi-disciplinary design optimization (MDO) opportunities that propeller-wing integration brings along, the present Thesis was designed with the objective of building a surrogate-based MDO framework for a general aviation aircraft featuring wing mounted tractor propellers. Such objective was achieved by developing appropriate analysis tools to model the most relevant effects of wing-propellers interaction, and by integrating them in suitable optimization architectures enhanced by the adoption of surrogate models. Two research hypotheses underlay such approach, the first claiming that accounting for wing-propeller interaction effects could lead to better designs, and the second claiming that the adoption of surrogate modeling techniques could greatly improve overall optimization performances. The successful accomplishment of the described objective was demonstrated by applying the optimization on an existing aircraft and achieving sensitive fuel savings. The mentioned hypotheses were instead proven under several aspects through the multiple surrogate-based optimization frameworks adopted and the obtained optimal designs. The work proposed as well innovative solutions to perform a full interaction wing-propellers analysis, such as routines to assess and model the propeller streamtube deflection and the wing swirl recovery effects. It also provided guidance for the implementation of surrogate-based optimizations in problems featuring high numbers of design variables and multiple complex non-linear constraints, testing different surrogate models, as well as different frameworks, to achieve local and global optimal designs.iii ACKNOWLEDGEMENTSThe path leading to the achievement of my Master in Aerospace Engineering has been a challenging and rewarding one, along which all my professors and colleagues at TU Delft have been a huge source of motivation and improvement.This Thesis is the culmination of such journey, and would not have been possible without the support of the people I have been working with over the past year. I would first like to thank my supervisor Dr. Elham of TU Delft for his availability and precious contribution in several aspects of the work. A great thanks is due as well to Professor Brian German who hosted me at the Georgia Institute o...

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“…Several wind tunnel and numerical studies have been dedicated to investigating the influence of propeller wake on the aerodynamic performance of a wing. [21][22][23][24] In the current research, a commercially manufactured Extra 300 3D and a custom-built Extra 260 were used to gather flight test data using a 16 camera motion tracking system. The lift and drag characteristics of both aircraft were obtained for free-flight conditions.…”

Section: Introductionmentioning

confidence: 99%

Glide and Powered Flight Characteristics of Micro Air Vehicles from Experimental Measurements

Rao

Uhlig

Selig

2012

30th AIAA Applied Aerodynamics Conference

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Aerodynamic characteristics of Micro Air Vehicles (MAVs) is not well addressed in aeronautics literature, and more experimental data are required to help better understand the behavior of fixed-wing MAVs. In the current research, aerodynamic characteristics of two MAVs were measured using a motion tracking system. The aircraft used were flat-foam surface, highly-aerobatic, micro RC models. Tests were conducted in glide and powered flight conditions to assess the aerodynamic performance of a commercially manufactured Extra 300 3D and a custom-built Extra 260 with wingspans of 42.67 cm (16.8 in) and 41.27 cm (16.25 in), respectively. The results presented show the longitudinal aerodynamic characteristics of the MAVs over a range of angle of attack at a nominal Reynolds number of 25,000. The influence of low Reynolds numbers effects on the aerodynamic characteristics and performance of the aircraft are discussed. The aerodynamic characteristics in powered flight were analyzed by testing the Extra 300 3D over a range of propeller advance ratios. Results indicate an increase in the slope of the lift curve and reduction in drag with decreasing propeller advance ratios.Nomenclature a x , a y , a z = body-axis translational accelerationairplane mass n = propeller rotational speed (rev/sec) p, q, r = roll, pitch and yaw rates R = transformation or rotation matrix Re = Reynolds number based on mean aerodynamic chord (V c/ν) S f = fuselage area S prop = propeller area S ref = reference area (wing area + fuselage area) S h = tail area S w = wing area u, v, w = body-fixed translational velocity V = inertial speed α = angle of attack α = angle of attack rate β = sideslip anglė β = rate of change of sideslip angle φ, θ, ψ = roll, pitch and heading angles ρ = density of air ν = kinematic viscosity ω = angular rates [ p q r ] T Subscripts ac = aircraft b= body-fixed frame E = Earth-fixed axis system f = due to fuselage G = due to gravity h = horizontal tail w = wing x, y, z = body-fixed axis system directions α, β = derivative per angle of attack or sideslip angle

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Propeller/wing interaction

Cited by 13 publications

References 5 publications

Experimental Investigation of Aerodynamic Interactions of a Wing with Deployed Fowler Flap under Influence of a Propeller Slipstream

Experimental Investigation of Aerodynamic Interactions of a Wing with Deployed Fowler Flap under Influence of a Propeller Slipstream

A Surrogate-Based Multi-Disciplinary Design Optimization Framework Exploiting Wing-Propeller Interaction

Glide and Powered Flight Characteristics of Micro Air Vehicles from Experimental Measurements

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