Consider a flat plate with a chord length (from leading to trailing edge) of 1 m. The free-strean flow properties are M1 = 3, p1 = 1 atm, and T1 = 270 K. Using shock-expansion theory, tabula and plot on graph paper these properties as functions of angle of attack from 0 to 30° (use increments of 5°): a. Pressure on the top surface b. Pressure on the bottom surface c. Temperature on the top surface d. Temperature on the bottom surface e. Lift per unit span f. Drag per unit span g. Lift/drag ratio
Consider a flat plate with a chord length (from leading to trailing edge) of 1 m. The free-strean flow properties are M1 = 3, p1 = 1 atm, and T1 = 270 K. Using shock-expansion theory, tabula and plot on graph paper these properties as functions of angle of attack from 0 to 30° (use increments of 5°): a. Pressure on the top surface b. Pressure on the bottom surface c. Temperature on the top surface d. Temperature on the bottom surface e. Lift per unit span f. Drag per unit span g. Lift/drag ratio
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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Transcribed Image Text:**Problem Statement: Supersonic Flow Over a Flat Plate**
Consider a flat plate with a chord length (from leading to trailing edge) of 1 m. The free-stream flow properties are \( M_1 = 3 \), \( p_1 = 1 \, \text{atm} \), and \( T_1 = 270 \, \text{K} \). Using shock-expansion theory, tabulate and plot on graph paper these properties as functions of angle of attack from 0 to 30° (use increments of 5°):
a. Pressure on the top surface
b. Pressure on the bottom surface
c. Temperature on the top surface
d. Temperature on the bottom surface
e. Lift per unit span
f. Drag per unit span
g. Lift/drag ratio
*(Note: The results from this problem will be used for comparison with linear supersonic theory in Chap. 9.)*
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