lecture #6 ehsan roohi sharif university of technology aerospace engineering department 1
TRANSCRIPT
![Page 1: Lecture #6 Ehsan Roohi Sharif University of Technology Aerospace Engineering Department 1](https://reader035.vdocument.in/reader035/viewer/2022062322/5697c01e1a28abf838cd142f/html5/thumbnails/1.jpg)
Lecture #6
Ehsan RoohiSharif University of Technology
Aerospace Engineering Department
1
![Page 2: Lecture #6 Ehsan Roohi Sharif University of Technology Aerospace Engineering Department 1](https://reader035.vdocument.in/reader035/viewer/2022062322/5697c01e1a28abf838cd142f/html5/thumbnails/2.jpg)
2
Wind Tunnel
Pressure Coefficient
![Page 3: Lecture #6 Ehsan Roohi Sharif University of Technology Aerospace Engineering Department 1](https://reader035.vdocument.in/reader035/viewer/2022062322/5697c01e1a28abf838cd142f/html5/thumbnails/3.jpg)
3
![Page 4: Lecture #6 Ehsan Roohi Sharif University of Technology Aerospace Engineering Department 1](https://reader035.vdocument.in/reader035/viewer/2022062322/5697c01e1a28abf838cd142f/html5/thumbnails/4.jpg)
4
![Page 5: Lecture #6 Ehsan Roohi Sharif University of Technology Aerospace Engineering Department 1](https://reader035.vdocument.in/reader035/viewer/2022062322/5697c01e1a28abf838cd142f/html5/thumbnails/5.jpg)
5
![Page 6: Lecture #6 Ehsan Roohi Sharif University of Technology Aerospace Engineering Department 1](https://reader035.vdocument.in/reader035/viewer/2022062322/5697c01e1a28abf838cd142f/html5/thumbnails/6.jpg)
6
![Page 7: Lecture #6 Ehsan Roohi Sharif University of Technology Aerospace Engineering Department 1](https://reader035.vdocument.in/reader035/viewer/2022062322/5697c01e1a28abf838cd142f/html5/thumbnails/7.jpg)
7
The kinetic energy per unit volume is called dynamic pressure q
The pressure energy per unit volume (due to random motion within the fluid) is the static pressure of the fluid and is given the symbol p
The constant energy per unit volume is called the total pressure pt.Bernoulli's equation reduces to
Dynamic pressure + Static pressure = Total pressure (7)
For rotational flow the total pressure pt is constant along a streamline but may vary from streamline to streamline.
HW: Read wiki page about Bernoulli equation and write a 2 pages report about different versions of this equation.
![Page 8: Lecture #6 Ehsan Roohi Sharif University of Technology Aerospace Engineering Department 1](https://reader035.vdocument.in/reader035/viewer/2022062322/5697c01e1a28abf838cd142f/html5/thumbnails/8.jpg)
8
![Page 9: Lecture #6 Ehsan Roohi Sharif University of Technology Aerospace Engineering Department 1](https://reader035.vdocument.in/reader035/viewer/2022062322/5697c01e1a28abf838cd142f/html5/thumbnails/9.jpg)
9
![Page 10: Lecture #6 Ehsan Roohi Sharif University of Technology Aerospace Engineering Department 1](https://reader035.vdocument.in/reader035/viewer/2022062322/5697c01e1a28abf838cd142f/html5/thumbnails/10.jpg)
10
Wind Tunnel
![Page 11: Lecture #6 Ehsan Roohi Sharif University of Technology Aerospace Engineering Department 1](https://reader035.vdocument.in/reader035/viewer/2022062322/5697c01e1a28abf838cd142f/html5/thumbnails/11.jpg)
11
![Page 12: Lecture #6 Ehsan Roohi Sharif University of Technology Aerospace Engineering Department 1](https://reader035.vdocument.in/reader035/viewer/2022062322/5697c01e1a28abf838cd142f/html5/thumbnails/12.jpg)
12
![Page 13: Lecture #6 Ehsan Roohi Sharif University of Technology Aerospace Engineering Department 1](https://reader035.vdocument.in/reader035/viewer/2022062322/5697c01e1a28abf838cd142f/html5/thumbnails/13.jpg)
13
![Page 14: Lecture #6 Ehsan Roohi Sharif University of Technology Aerospace Engineering Department 1](https://reader035.vdocument.in/reader035/viewer/2022062322/5697c01e1a28abf838cd142f/html5/thumbnails/14.jpg)
14
![Page 15: Lecture #6 Ehsan Roohi Sharif University of Technology Aerospace Engineering Department 1](https://reader035.vdocument.in/reader035/viewer/2022062322/5697c01e1a28abf838cd142f/html5/thumbnails/15.jpg)
15
![Page 16: Lecture #6 Ehsan Roohi Sharif University of Technology Aerospace Engineering Department 1](https://reader035.vdocument.in/reader035/viewer/2022062322/5697c01e1a28abf838cd142f/html5/thumbnails/16.jpg)
16
![Page 17: Lecture #6 Ehsan Roohi Sharif University of Technology Aerospace Engineering Department 1](https://reader035.vdocument.in/reader035/viewer/2022062322/5697c01e1a28abf838cd142f/html5/thumbnails/17.jpg)
17
Cp depends on Reynolds Number and body shape
![Page 18: Lecture #6 Ehsan Roohi Sharif University of Technology Aerospace Engineering Department 1](https://reader035.vdocument.in/reader035/viewer/2022062322/5697c01e1a28abf838cd142f/html5/thumbnails/18.jpg)
18
![Page 19: Lecture #6 Ehsan Roohi Sharif University of Technology Aerospace Engineering Department 1](https://reader035.vdocument.in/reader035/viewer/2022062322/5697c01e1a28abf838cd142f/html5/thumbnails/19.jpg)
19
Boundary Conditions
![Page 20: Lecture #6 Ehsan Roohi Sharif University of Technology Aerospace Engineering Department 1](https://reader035.vdocument.in/reader035/viewer/2022062322/5697c01e1a28abf838cd142f/html5/thumbnails/20.jpg)
20
HW’sChapter 3: P. 1-7In four weeks