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.16 Using shock-expansion theory, calculate the lift and drag (in pounds) on a symmetrical diamond airfoil of semiangle ɛ = of attack to the free stream of 5° when the upstream Mach number and pressure are 2.0 and 2116 lb/ft², respectively. The maximum thickness of the airfoil is t = 0.5 ft. Assume a unit length of 1 ft in the span direction (perpendicular to the page in Fig. 4.35). 15° (see Fig. 4.35) at an angle

.16 Using shock-expansion theory, calculate the lift and drag (in pounds) on a symmetrical diamond airfoil of semiangle ɛ = of attack to the free stream of 5° when the upstream Mach number and pressure are 2.0 and 2116 lb/ft², respectively. The maximum thickness of the airfoil is t = 0.5 ft. Assume a unit length of 1 ft in the span direction (perpendicular to the page in Fig. 4.35). 15° (see Fig. 4.35) at an angle

Elements Of Electromagnetics
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
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4.16 Using shock-expansion theory, calculate the lift and drag (in pounds) on a symmetrical diamond airfoil of semiangle e = of attack to the free stream of 5° when the upstream Mach number and pressure are 2.0 and 2116 lb/ft², respectively. The maximum thickness of the airfoil is t= 15° (see Fig. 4.35) at an angle 0.5 ft. Assume a unit length of 1 ft in the span direction (perpendicular to the page in Fig. 4.35).
Transcribed Image Text:4.16 Using shock-expansion theory, calculate the lift and drag (in pounds) on a symmetrical diamond airfoil of semiangle e = of attack to the free stream of 5° when the upstream Mach number and pressure are 2.0 and 2116 lb/ft², respectively. The maximum thickness of the airfoil is t= 15° (see Fig. 4.35) at an angle 0.5 ft. Assume a unit length of 1 ft in the span direction (perpendicular to the page in Fig. 4.35).
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