Hood Figure 12.5 Lockheed F-104.
Refrigeration and Air Conditioning Technology (MindTap Course List)
8th Edition
ISBN:9781305578296
Author:John Tomczyk, Eugene Silberstein, Bill Whitman, Bill Johnson
Publisher:John Tomczyk, Eugene Silberstein, Bill Whitman, Bill Johnson
Chapter24: Expansion Devices
Section: Chapter Questions
Problem 9RQ: The three factors that determine the capacity of a T XV are ______, ______, and _____.
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Consider the same Lockheed F-104 supersonic fighter shown, with the same flight conditions of Mach 2 at an altitude of 11 km. For these conditions the wing angle of attack is α = 0.035 rad = 1.98◦. Assume the chord length of the airfoil is 2.2 m, which is approximately the mean chord length for the wing. Also, assume fully turbulent flow over the airfoil. Calculate: (a) the airfoil skin friction drag coefficient, and (b) the airfoil wave-drag coefficient. Compare the two values of drag.
![Hood
Figure 12.5 Lockheed F-104.](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2F00dee94b-1ba5-4ca4-9d3b-d4d569adf185%2Fae51602e-1f4a-4eb9-b1fb-d6a84ac17096%2Fuyspobe.png&w=3840&q=75)
Transcribed Image Text:Hood
Figure 12.5 Lockheed F-104.
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