A commercial aircraft (with a mass of 71411 kg, wing surface area of 119 m² and wing aspect ratio of 10) produces a maximum of 209459 newtons of thrust. Assuming CLMAX = 2.1 and CD Calculate the Climb Rate (in feet/min) at an initial climb airspeed of 169 knots. -89 O 11.79 3570.55 171697.81 2320.13 = 0.06,
A commercial aircraft (with a mass of 71411 kg, wing surface area of 119 m² and wing aspect ratio of 10) produces a maximum of 209459 newtons of thrust. Assuming CLMAX = 2.1 and CD Calculate the Climb Rate (in feet/min) at an initial climb airspeed of 169 knots. -89 O 11.79 3570.55 171697.81 2320.13 = 0.06,
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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![A commercial aircraft (with a mass of 71411 kg, wing surface area of 119 m² and wing aspect ratio of 10) produces a maximum of 209459 newtons of thrust. Assuming CLMAX = 2.1 and CD
Calculate the Climb Rate (in feet/min) at an initial climb airspeed of 169 knots.
-89
O 11.79
3570.55
171697.81
2320.13
= 0.06,](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F89579140-fe37-4be9-a0a7-6927a5b3e229%2Fcb9a80ca-2bd1-4fa1-98fa-4383f16ecf22%2Fhuojzv6_processed.jpeg&w=3840&q=75)
Transcribed Image Text:A commercial aircraft (with a mass of 71411 kg, wing surface area of 119 m² and wing aspect ratio of 10) produces a maximum of 209459 newtons of thrust. Assuming CLMAX = 2.1 and CD
Calculate the Climb Rate (in feet/min) at an initial climb airspeed of 169 knots.
-89
O 11.79
3570.55
171697.81
2320.13
= 0.06,
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