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 21 May 2017 My Price 7.00

Determine the static pressure rise across the diffuser and the exit area

An aircraft flies with a Mach number Ma1 =0.8 at an altitude of 7000 m where the pressure is 41.1 kPa and the temperature is 242.7 K. The diffuser at the engine inlet has an exit Mach number of Ma2 =0.3. For a mass flow rate of 65 kg/s, determine the static pressure rise across the diffuser and the exit area.

 

Answers

Alpha Geek
(8)
Status NEW Posted 21 May 2017 03:05 PM My Price 7.00

-----------

Attachments

1495382256-1547677_1_636308844990629356_1.jpg
1495382257-1547677_2_636308844990629356_2.jpg
1495382260-1547677_3_636308844990629356_3.jpg
Not Rated(0)