Consider a Pitot static tube mounted on the nose of an experimental airplane. A Pitot tube measures the total pressure at the tip of the probe (hence sometimes called the Pitot pressure), and a Pitot static tube combines this with a simultaneous measurement of the free-stream static pressure. The Pitot and free-stream static measurements are given below for three different flight conditions. Calculate the free-stream Mach number at which the airplane is flying for each of the three different conditions: a. Pitot pressure = 1.22 × 105 N/m², static pressure = 1.01 × 105 N/m² b. Pitot pressure = 7222 lb/ft², static pressure = 2116 lb/ft² c. Pitot pressure = 13107 lb/ft², static pressure = 1020 lb/ft²
Consider a Pitot static tube mounted on the nose of an experimental airplane. A Pitot tube measures the total pressure at the tip of the probe (hence sometimes called the Pitot pressure), and a Pitot static tube combines this with a simultaneous measurement of the free-stream static pressure. The Pitot and free-stream static measurements are given below for three different flight conditions. Calculate the free-stream Mach number at which the airplane is flying for each of the three different conditions: a. Pitot pressure = 1.22 × 105 N/m², static pressure = 1.01 × 105 N/m² b. Pitot pressure = 7222 lb/ft², static pressure = 2116 lb/ft² c. Pitot pressure = 13107 lb/ft², static pressure = 1020 lb/ft²
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:Consider a Pitot static tube mounted on the nose of an experimental airplane.
A Pitot tube measures the total pressure at the tip of the probe (hence
sometimes called the Pitot pressure), and a Pitot static tube combines this
with a simultaneous measurement of the free-stream static pressure. The Pitot
and free-stream static measurements are given below for three different flight
conditions. Calculate the free-stream Mach number at which the airplane is
flying for each of the three different conditions:
a. Pitot pressure = 1.22 × 105 N/m², static pressure = 1.01 × 105 N/m²
b. Pitot pressure = 7222 lb/ft², static pressure = 2116 lb/ft²
c. Pitot pressure = 13107 lb/ft², static pressure = 1020 lb/ft²
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