1. Derive . (6.80) and (6.81). 6.15 Derive Eqs. (6.86) and (6.87). 2. Estimate the sea-level liftoff distance for the airplane in Prob. 6.3. Assume a paved runway. Also, during the ground roll, the angle of attack is restricted by the requirement that the tail not drag the ground. Hence, assume that CL.mu during the ground roll is limited to 0.8. When the airplane is on the ground, the wings are 5 above the ground. Prob. 6.3. Consider an airplane patterned after the Fairchild Republic A-1 0, a twin-jet attack aircraft. The airplane has the following characteristics: wing area = 47m2, aspect ratio = 6.5, Oswald efficiency factor = 0.87, weight = 103, 047N, and zero-lift drag coefficient = 0.032. The airplane is equipped with two jet engines with 40,298 N of static thrust each at sea level. a. Calculate and plot the power-required curve at sea level. b. Calculate the maximum velocity at sea level. c. Calculate and plot the power-required curve at 5-km altitude. d. Calculate the maximum velocity at 5-km altitude. {Assume the engine thrust varies directly with free-stream density.)
We Write Essays for Students
Tell us about your assignment and we will find the best writer for your paper
Get Help Now!
PLACE THIS ORDER OR A SIMILAR ORDER WITH LITE ESSAYS TODAY AND GET AN AMAZING DISCOUNT
The post Calculate and plot the power-required curve at sea level. appeared first on Cheapest Academic Custom Papers.
Welcome to originalessaywriters.com, our friendly and experienced essay writers are available 24/7 to complete all your assignments. We offer high-quality academic essays written from scratch to guarantee top grades to all students. All our papers are 100% plagiarism-free and come with a plagiarism report, upon request
Tell Us “Write My Essay for Me” and Relax! You will get an original essay well before your submission deadline.
