Flight tests of a supersonic natural laminar flow airfoil

Frederick, Michael A.; Banks, David C.; Garzon, G. A.; Matisheck, Jason

doi:10.1088/0957-0233/26/6/064003

Cited by 8 publications

(3 citation statements)

References 12 publications

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“…On the other hand, flight tests on small and large motorised aircrafts of very different kinds have featured at least one or two IR cameras. Besides, laminar-turbulent transition detection is used in industry and research facilities worldwide for the sub-, trans-and supersonic flight tests (Frederick et al 2015).…”

Section: Common Use Cases For Thermographic Measurementmentioning

confidence: 99%

Automatic separation of laminar-turbulent flows on aircraft wings and stabilisers via adaptive attention butterfly network

2022

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Many of the laminar-turbulent flow localisation techniques are strongly dependent upon expert control even-though determining the flow distribution is the prerequisite for analysing the efficiency of wing & stabiliser design in aeronautics. Some recent efforts have dealt with the automatic localisation of laminar-turbulent flow but they are still in infancy and not robust enough in noisy environments. This study investigates whether it is possible to separate flow regions with current deep learning techniques. For this aim, a flow segmentation architecture composed of two consecutive encoder-decoder is proposed, which is called Adaptive Attention Butterfly Network. Contrary to the existing automatic flow localisation techniques in the literature which mostly rely on homogeneous and clean data, the competency of our proposed approach in automatic flow segmentation is examined on the mixture of diverse thermographic observation sets exposed to different levels of noise. Finally, in order to improve the robustness of the proposed architecture, a self-supervised learning strategy is adopted by exploiting 23.468 non-labelled laminar-turbulent flow observations.

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Section: Common Use Cases For Thermographic Measurementmentioning

confidence: 99%

Automatic separation of laminar-turbulent flows on aircraft wings and stabilisers via adaptive attention butterfly network

2022

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“…The existing mature online testing method of aircraft flow field is mainly infrared thermal imaging method [12][13][14], which maintains the quasi-insulation wall by coating the insulating material to obtain the visual boundary layer state. However, this method cannot obtain the magnitude of wall shear stress or pressure quantitatively.…”

Section: Introductionmentioning

confidence: 99%

Flexible skin for measurement of boundary layer state and flight attitude identification on UAV

Pang

Zhao²,

Zhong

et al. 2023

Smart Mater. Struct.

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The wall shear stress and pressure are important for analyzing boundary layer flow and evaluating the aerodynamic performance of the aircraft. In this study, a flexible skin consisting of dual layer hot-film sensors and pressure belts was developed to measure the distribution of wall shear stress and pressure on an unmanned aerial vehicle (UAV) during increase of angle of attack (AOA), tail spin, and decreases of AOA. The sensitivity of the dual layer hot-film sensor is improved by about 150% due to heat conduction reduced. The relative error of pressure belt is less than 1% at 10-65℃. The boundary layer separation and reattachment time, separation AOA and time-shift of the flow field changes in flight conditions are determined. The separated AOA of the left and right wing boundary layers are 26.41° and 17.58° respectively. There is a delay about four seconds between the separation of the boundary layer and the entry of the tail spin, which can provide early warning to prevent abnormal flight conditions such as post stall and tail spin.

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“…Separate studies by NASA [2] and JAXA [3] have focused on the boom signature reduction with experimental campaigns on their scaled models. In terms of drag-reduction, natural laminar flow (NLF) technology has shown promising results [4,5,6]. On the other hand, multidisciplinary (MDO) and aerodynamic shape optimization (ASO) techniques offer a powerful and possibly essential approach to design an efficient supersonic aircraft [7].…”

Section: Introductionmentioning

confidence: 99%

Multipoint Aerodynamic Shape Optimization for Subsonic and Supersonic Regimes

Mangano

Martins

2019

AIAA Scitech 2019 Forum

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The second-generation of supersonic civil transport has to match ambitious targets in terms of noise reduction and efficiency to become economically and environmentally viable. High-fidelity numerical optimization offers a powerful approach to address the complex trade-offs intrinsic to this novel configuration. Past and current research has proven the potential of supersonic aircraft shape optimization but lacks deeper insight on final layouts. This work partially fills this gap by investigating RANS-based aerodynamic optimization for both supersonic, transonic and subsonic conditions. We perform single and multi-point optimization to minimize the drag over an ideal supersonic aircraft flight envelope and assess the influence of physical and numerical parameters on optimization accuracy and robustness. Leading and trailing edge morphing capabilities are introduced to improve the efficiency at transonic and subsonic flight speed by relaxing the trade-offs on clean shape optimization. Benefits in terms of drag reduction are quantified and benchmarked with fixed-edges results. We observe how the optimized airfoils outperform baseline reference shapes from a minimum of 4% up to 86% for different design cases and flight conditions. The study is then extended to the optimization of a planar, low-aspect-ratio, and low-sweep wing, using the same schematic approach of 2D analysis. We investigate the influence of wing twist alone and twist and shape on cruise performance, obtaining a drag reduction of 6% and 25% respectively as the optimizer copes with both viscosity and compressibility effects over the wing. Preliminary results for 3D multi-point optimization suggest that the proposed strategy enables a fast and effective design of highly-efficient wings, with drag reduction ranging from a minimum of 24% up to 74% for cruise at different speeds and altitudes. The benefits of RANS-based aerodynamic shape optimization to capture non-intuitive design trade-offs and offer deeper physical insight are ultimately discussed and quantified.

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Flight tests of a supersonic natural laminar flow airfoil

Cited by 8 publications

References 12 publications

Automatic separation of laminar-turbulent flows on aircraft wings and stabilisers via adaptive attention butterfly network

Automatic separation of laminar-turbulent flows on aircraft wings and stabilisers via adaptive attention butterfly network

Flexible skin for measurement of boundary layer state and flight attitude identification on UAV

Multipoint Aerodynamic Shape Optimization for Subsonic and Supersonic Regimes

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