NACA 0012 Airfoil Meshing - 搜索视频

全部
图片
视频
地图
资讯
购物
更多
笔记本

为你精选

我的播放列表

时长
全部短(小于 5 分钟)中(5-20 分钟)长(大于 20 分钟)
日期
全部过去 24 小时过去一周过去一个月去年
清晰度
全部低于 360p 360p 或更高 480p 或更高 720p 或更高 1080p 或更高
源
全部
Dailymotion
Vimeo
Metacafe
Hulu
VEVO
Myspace
MTV
CBS
Fox
CNN
MSN
价格
全部免费付费
重置

安全搜索:
中等
严格中等（默认）关闭

筛选器

最匹配的结果

Validating fundamentals: 2D NACA 0012 Airfoil Validation - Femto Engineering

Validating fundamentals: 2D NACA 0012 Airfoil Validation - Femto Engineering

2022年5月23日

Consider the NACA0012 airfoil. From the thin airfoil theory, a... | Filo

Consider the NACA0012 airfoil. From the thin airfoil theory, a... | Filo

已浏览 5134 次6 个月之前

In a lift-and-drag experiment performed in a wind tunnel, an NACA0012 airfoil was used. The airfoil has a 15 cm chord and a span length of 45 cm. Using a force measuring device, a lift force of 60 N was measured on the airfoil for a Reynolds number of 4.586 ×10^5. The lift coefficient for this airfoil is given by CL=2 πsinα, where αis the angle of attack. Under the given conditions, what is the angle of attack in degrees? | Numerade

In a lift-and-drag experiment performed in a wind tunnel, an NACA0012 airfoil was used. The airfoil has a 15 cm chord and a span length of 45 cm. Using a force measuring device, a lift force of 60 N was measured on the airfoil for a Reynolds number of 4.586 ×10^5. The lift coefficient for this airfoil is given by CL=2 πsinα, where αis the angle of attack. Under the given conditions, what is the angle of attack in degrees? | Numerade

Analysis of NACA0012 Airfoil For Different Angle of Attacks - Student Projects

Analysis of NACA0012 Airfoil For Different Angle of Attacks - Student Projects

2023年4月21日

SOLVED: Calculate the lift and drag force on a NACA 0012 airfoil with standard roughness at Re=6 million operating at 9 degrees angle of attack in a relative wind of 10 m/s, with a chord of 5 meters and a length of 5 meters in a standard atmosphere. Use the theory of wing sections curves from PPT.Update: In the problem, the line corresponding to section drag coefficient curve originating from cl corresponding to 9 degrees does not intersect. You can estimate it to:CL = 0.87Cd = 0.020Angle of att

SOLVED: Calculate the lift and drag force on a NACA 0012 airfoil with standard roughness at Re=6 million operating at 9 degrees angle of attack in a relative wind of 10 m/s, with a chord of 5 meters and a length of 5 meters in a standard atmosphere. Use the theory of wing sections curves from PPT.Update: In the problem, the line corresponding to section drag coefficient curve originating from cl corresponding to 9 degrees does not intersect. You can estimate it to:CL = 0.87Cd = 0.020Angle of att

2023年6月8日

✅ Ansys Fluent - NACA Airfoil 4412 - CFD.NINJA

✅ Ansys Fluent - NACA Airfoil 4412 - CFD.NINJA

已浏览 9034 次2017年9月10日

✅ Ansys CFX - NACA 0012 with Angle of Attack (AOA) - CFD.NINJA

✅ Ansys CFX - NACA 0012 with Angle of Attack (AOA) - CFD.NINJA

已浏览 4981 次2020年3月17日

NACA 0012 Airfoil, Compressible Flow CFD Simulation - MR CFD

2020年4月6日

Ansys of 2D NACA 0012 Airfoil using Fluent part 2

已浏览 153 次7 个月之前

YouTubeMaddy SAM

ANSYS Simulation of a Symmetrical airfoil NACA 0012 using rectangular domain

已浏览 117 次10 个月之前

YouTubeThara A Sanal

NACA 0012 airfoil at a large angle of attack of 25 degree

已浏览 484 次2 周前

YouTubeCFD Support

[FLUENT] NACA 0012 #3: Grid generation

已浏览 22 次5 个月之前

YouTubeJeonglae Kim

[FLUENT] NACA 0012 #1: Generating pointwise data on airfoil surface

已浏览 119 次5 个月之前

YouTubeJeonglae Kim

Prefoam Version 2.0: NACA 0012 Airfoil Meshing (Part 2)

YouTubeTemiz CFD

10° Tilted NACA 0012 pitching motion with mesh

已浏览 316 次2016年6月13日

YouTubeAeromines Media

HOW TO CREATE A BODY FITTING MESH FOR NACA 2412 AIRFOIL||MESHING TECHNIQUE CFD||AERO HUB

已浏览 306 次2022年7月15日

YouTubeAERO HUB

DNS Naca 0012 Re=30000 Aoa=12°

已浏览 9500 次2010年1月7日

YouTubeVincent Chapin

Airfoil NACA 0012 O-type Meshing in Gambit

已浏览 1977 次2018年5月31日

YouTubeIntroduction To CFD

Tutorial 8 - Part 3 - Flow over a NACA 0012 airfoil - Incompressible and compressible case setup.

已浏览 587 次2021年5月4日

Turbulent Flow Around Naca 0012 Airfoil Ansys Fluent step #4 Solution and Results شرح بالعربي

已浏览 1136 次2020年5月24日

YouTubeهندسة بالعربي

Ansys of 2D NACA 0012 Airfoil using Fluent part 1

已浏览 247 次7 个月之前

YouTubeMaddy SAM

ICEM CFD NACA-0012

已浏览 2338 次2015年4月11日

YouTubeMohamed Sereez

[FLUENT] NACA 0012 #5: Running simulation

已浏览 54 次5 个月之前

YouTubeJeonglae Kim

NACA 0012 - Airfoil CFD Simulation with OpenFOAM

已浏览 206 次11 个月之前

YouTubeTemiz CFD

Airfoil Aerodynamics (NACA 0012) Ux Velocity Component at AOF25DEG, DES KW

已浏览 812 次2023年8月16日

YouTubeCFD Support

Prefoam Version 2.0: NACA 0012 Airfoil Geometry Creation (Part 1)

已浏览 1 次3 周前

YouTubeTemiz CFD

Prefoam Version 2.0: NACA 0012 Airfoil Geometry Creation (Part 1)

YouTubeTemiz CFD

SALOME + OpenFOAM Tutorial: NACA 0012 Airfoil Part 4

已浏览 5624 次2017年11月5日

YouTubeAli Ikhsanul

Flow around NACA 0012 Airfoil | ANSYS FLUENT

已浏览 56 次4 个月之前

YouTubeCFD World

Airfoil Mesh Velocity inlet flow over an NACA 0012 Airfoil

已浏览 63 次11 个月之前

YouTubeNMIT Aero Department

观看更多视频

静态缩略图占位符

报告不当内容

请选择下列任一选项。

无关

低俗内容

成人

儿童性侵犯

© 2024 Microsoft

隐私声明和 Cookie
法律声明
广告
关于我们的广告
帮助
反馈
消费者健康隐私