Pu Wings at supersonic flows can be modeled as a flat plate that have constant pressure distributions across their chord. Ignoring any viscous effects determine the drag force of the wing section. Round to the full N/m and make sure you use the standard sign convention (i.e. right hand rule). Use the following data chord = 1.5 m epsilon = 5 degree angle of attack = 20.0 alpha upper surface pressure = 60,000 Pa lower surface pressure = 150,000 Pa %3D

Pu Wings at supersonic flows can be modeled as a flat plate that have constant pressure distributions across their chord. Ignoring any viscous effects determine the drag force of the wing section. Round to the full N/m and make sure you use the standard sign convention (i.e. right hand rule). Use the following data chord = 1.5 m epsilon = 5 degree angle of attack = 20.0 alpha upper surface pressure = 60,000 Pa lower surface pressure = 150,000 Pa %3D

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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Question

Pu
Wings at supersonic flows can be modeled as a flat plate that have constant pressure
distributions across their chord. Ignoring any viscous effects determine the drag
force of the wing section.
Round to the full N/m and make sure you use the standard sign convention (i.e. right
hand rule).
Use the following data
chord = 1.5 m
epsilon = 5 degree
angle of attack = 20.0 alpha
upper surface pressure = 60,000 Pa
lower surface pressure = 150,000 Pa

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