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A fuel tank in wing has dimensions in Fig. 1, where the width is equal to the height and the tank is half full. The aircraft undergoes lateral acceleration due to non-zero sideslip, but level flight with level wings. The aircraft is flying at an altitude of 20000ft in ISA+0. The velocity of the aircraft is V=160m/s, with a radius of 5000m. The tanks vents to a port that is 250Pa above the freestream static pressure. The fuel has a specific gravity of 0.825. Use g=9.80665m/s². Calculate the absolute pressure at point A. h W Lateral direction Point A

A fuel tank in wing has dimensions in Fig. 1, where the width is equal to the height and the tank is half full. The aircraft undergoes lateral acceleration due to non-zero sideslip, but level flight with level wings. The aircraft is flying at an altitude of 20000ft in ISA+0. The velocity of the aircraft is V=160m/s, with a radius of 5000m. The tanks vents to a port that is 250Pa above the freestream static pressure. The fuel has a specific gravity of 0.825. Use g=9.80665m/s². Calculate the absolute pressure at point A. h W Lateral direction Point A

Elements Of Electromagnetics
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
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A fuel tank in wing has dimensions in Fig. 1, where the width is equal to the height and the tank is half full. The aircraft undergoes lateral acceleration due to non-zero sideslip, but level flight with level wings. The aircraft is flying at an altitude of 20000ft in ISA+0. The velocity of the aircraft is V=160m/s, with a radius of 5000m. The tanks vents to a port that is 250Pa above the freestream static pressure. The fuel has a specific gravity of 0.825. Use g=9.80665m/s². Calculate the absolute pressure at point A. h W Lateral direction Point A 1₁ Figure 1. Fuel tank undergoing lateral acceleration
Transcribed Image Text:A fuel tank in wing has dimensions in Fig. 1, where the width is equal to the height and the tank is half full. The aircraft undergoes lateral acceleration due to non-zero sideslip, but level flight with level wings. The aircraft is flying at an altitude of 20000ft in ISA+0. The velocity of the aircraft is V=160m/s, with a radius of 5000m. The tanks vents to a port that is 250Pa above the freestream static pressure. The fuel has a specific gravity of 0.825. Use g=9.80665m/s². Calculate the absolute pressure at point A. h W Lateral direction Point A 1₁ Figure 1. Fuel tank undergoing lateral acceleration
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