2018 Atmospheric and Space Environments Conference最新文献_第2页

An Experimental Study on the Durability of Icephobic Slippery Liquid-Infused Porous Surfaces (SLIPS) Pertinent to Aircraft Anti-/De-Icing 飞机防/除冰用疏冰湿性液体注入多孔表面耐久性实验研究

2018 Atmospheric and Space Environments Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-3654

Liqun Ma, Zichen Zhang, Yang Liu, Hui Hu

{"title":"An Experimental Study on the Durability of Icephobic Slippery Liquid-Infused Porous Surfaces (SLIPS) Pertinent to Aircraft Anti-/De-Icing","authors":"Liqun Ma, Zichen Zhang, Yang Liu, Hui Hu","doi":"10.2514/6.2018-3654","DOIUrl":"https://doi.org/10.2514/6.2018-3654","url":null,"abstract":"Recently, bio-inspired surfaces have been found to be hydrophobic and/or icephobic, which has very low adhesion force for water and/or ice. When bio-inspired surfaces are applied for aircraft icing mitigation, they would suffer erosions due to high-speed impacting of the water droplets in the form of fog/mist. However, the knowledge of the coating durability regarding spray erosion is still quite limited. In the present study, an experimentally investigation was conducted to evaluate the durability of a PTFE membrane based slippery liquid infused porous surface (SLIPS) subject to water spray erosion, in comparison to that of a commonly used superhydrophobic surface (SHS) coating (i.e., a commercially-available Hydrobead® SHS coating). A wind driven spray generator was established with the spray erosion speed controllable from 45 m/s to 95 m/s. The anti-icing performance of the SHS and the SLIPS was validated in an icing research wind tunnel. Impact dynamics of individual water droplets at high Weber number about 3,000 and water spray erosion process of the SHS and the SLIPS were compared. The wettability-based coating lifetime was analyzed by measuring the dynamic contact angles on the SHS and the SLIPS under water spray erosions with different velocities. A cumulative-fatigue-damage theory was used to help predict the coating life time for in-flight aircraft icing mitigation. It turns out that the SLIPS could maintain its hydrophobicity better than the SHS under a moderate spray erosion speed. The mechanism of the spray erosion process for the SHS and the SLIPS was also examined in this study.","PeriodicalId":419456,"journal":{"name":"2018 Atmospheric and Space Environments Conference","volume":"26 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121592877","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 3

An Experimental Investigation on an Electric-Thermal Strategy for Wind Turbines Icing Mitigation 风电机组减冰电热策略试验研究

2018 Atmospheric and Space Environments Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-3658

Linyue Gao, Yang Liu, Cem Kolbakir, Hui Hu

引用次数: 4

Experimental Measurement of Ice Accretion Rate in Mixed-phase Icing Cloud 混合相结冰云中冰积速率的实验测量

2018 Atmospheric and Space Environments Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-4222

Sihong Yan, J. Palacios

引用次数: 0

Partially Melting of a Suspended Ice Particle under Forced Advection-Diffusion 强迫平流-扩散作用下悬浮冰粒的部分熔化

2018 Atmospheric and Space Environments Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-4221

Yiqiang Han, S. Kala, Sihong Yan, J. Palacios

引用次数: 0

Summary of Ice Shape Geometric Fidelity Studies on an Iced Swept Wing 结冰后掠翼冰形几何保真度研究综述

2018 Atmospheric and Space Environments Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-3494

B. Woodard, Andy P. Broeren, Sam Lee, Christopher W. Lum, M. Bragg

{"title":"Summary of Ice Shape Geometric Fidelity Studies on an Iced Swept Wing","authors":"B. Woodard, Andy P. Broeren, Sam Lee, Christopher W. Lum, M. Bragg","doi":"10.2514/6.2018-3494","DOIUrl":"https://doi.org/10.2514/6.2018-3494","url":null,"abstract":"Understanding the aerodynamic impact of swept-wing ice accretions is a crucial component of the design of modern aircraft. Computer-simulation tools are commonly used to approximate ice shapes, so the necessary level of detail or fidelity of those simulated ice shapes must be understood relative to high-fidelity representations of the ice. Previous tests were performed in the NASA Icing Research Tunnel to acquire high-fidelity ice shapes. Some of those ice shapes are based on aircraft certification requirements. From this database, full-span artificial ice shapes were designed and manufactured for both an 8.9%-scale and 13.3%-scale semispan wing model of the CRM65 which has been established as the full-scale baseline for this swept-wing project. These models were tested in the Walter H. Beech wind tunnel at Wichita State University and at the ONERA F1 facility, respectively. The data collected in the Wichita St. University wind tunnel provided a low-Reynolds number baseline study while the pressurized F1 facility produced data over a wide range of Reynolds and Mach numbers with the highest Reynolds number studied being approximately Re = 11.9×10 6 . Three different fidelity representations were created based on three different icing conditions. Lower-fidelity ice shapes were created by lofting a smooth ice shape between cross-section cuts of the high-fidelity ice shape. Grit roughness was","PeriodicalId":419456,"journal":{"name":"2018 Atmospheric and Space Environments Conference","volume":"100 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116994041","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 18

A Novel Method for Constructing Analog Roughness Patterns to Replicate Ice Accretion Characteristics 构建模拟粗糙度模式以复制冰增生特征的新方法

2018 Atmospheric and Space Environments Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-3015

John‐Mark Clemenson, T. Shannon, S. McClain

引用次数: 3

IDDES simulation of flow separation on an 3-D NACA23012 airfoil with spanwise ridge ice 带展向脊冰的NACA23012翼型流动分离的IDDES模拟

2018 Atmospheric and Space Environments Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-2862

Shufan Hu, Chen Zhang, Hong Liu, Fuxin Wang, Yanxin Li

引用次数: 6

Aerodynamic, Laser Scanning and Photogrammetric Measurements of Cold Soaked Fuel Frost 冷浸燃料霜的气动、激光扫描和摄影测量

2018 Atmospheric and Space Environments Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-3830

E. Soinne, T. Rosnell

{"title":"Aerodynamic, Laser Scanning and Photogrammetric Measurements of Cold Soaked Fuel Frost","authors":"E. Soinne, T. Rosnell","doi":"10.2514/6.2018-3830","DOIUrl":"https://doi.org/10.2514/6.2018-3830","url":null,"abstract":"After an aircraft landing during a stopover Cold Soaked Fuel Frost is often formed on the wing even at temperatures above 0 o C. It is of interest to measure the frost geometry and corresponding aerodynamic effect on lift coefficient. To investigate these effects a HL-CRM wing model, representing the wing of a modern jet aircraft, was built including a wing tank cooling system. Real frost was generated on the wing in a wind tunnel test section and the frost thickness was measured with an Elcometer gauge. Frost surface geometry was measured with laser scanning and photogrammetry. The measurements were made with titanium dioxide painting to enhance surface reflectivity and without painting. The accuracy of laser scanning and photogrammetry were compared in these four cases. The aerodynamic effect of the frost was studied in a simulated aircraft take-off sequence, in which the speed was accelerated to a typical rotation speed and the wing model was then rotated to an angle of attack used at initial climb. Time histories of the lift coefficient were measured with a force balance. Time histories of the upper surface boundary layer displacement thickness were measured with a boundary layer rake. The measurements showed that depending on the ambient temperature the frost may evaporate/melt during the take-off sequence. Highest lift losses occurred after the rotation. The lift losses correlated with average frost thickness and the increase of the boundary layer displacement thickness.","PeriodicalId":419456,"journal":{"name":"2018 Atmospheric and Space Environments Conference","volume":"2 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-06-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132619366","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 3

Wake Turbulence Evolution and Hazard Analysis for a General Aviation Takeoff Accident 某通用航空起飞事故尾流演化及危害分析

2018 Atmospheric and Space Environments Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-3019

C. Schwarz, D. Fischenberg, F. Holzäpfel

引用次数: 2

Numerical Investigation of Particle Breakup and Ingestion into an Axial Low Pressure Compressor at Engine Icing Operating Points 发动机结冰工况下轴向低压压气机颗粒破碎与吸入的数值研究

2018 Atmospheric and Space Environments Conference Pub Date : 2018-06-24 DOI: 10.2514/6.2018-4131

D. Rigby, W. Wright

引用次数: 2