Alpha Geek

(8)

$10/per page/Negotiable

About Alpha Geek

Levels Tought:
University

Expertise:
Accounting,Algebra See all
Accounting,Algebra,Architecture and Design,Art & Design,Biology,Business & Finance,Calculus,Chemistry,Communications,Computer Science,Environmental science,Essay writing,Programming,Social Science,Statistics Hide all
Teaching Since: Apr 2017
Last Sign in: 438 Weeks Ago, 2 Days Ago
Questions Answered: 9562
Tutorials Posted: 9559

Education

  • bachelor in business administration
    Polytechnic State University Sanluis
    Jan-2006 - Nov-2010

  • CPA
    Polytechnic State University
    Jan-2012 - Nov-2016

Experience

  • Professor
    Harvard Square Academy (HS2)
    Mar-2012 - Present

Category > Applied Sciences Posted 31 Jul 2017 My Price 8.00

Calculate the stagnation pressure and Mach number upstream of the shock

Air enters a normal shock at 22.6 kPa, 217 K, and 680 m/s. Calculate the stagnation pressure and Mach number upstream of the shock, as well as pressure, temperature, velocity, Mach number, and stagnation pressure downstream of the shock.

 

 

Answers

Alpha Geek
(8)
Status NEW Posted 31 Jul 2017 11:07 AM My Price 8.00

-----------

Attachments

1501500313-1547804_2_636369025865444050_15013056888071689003619.jpg
1501500313-1547804_3_636369025865444050_1501305733334-5227828.jpg
1501500351-1547804_1_636369025865444050_15013056706791516140634.jpg
Not Rated(0)