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Consider the supersonic flow over a 5° half-angle wedge at zero angle of attack, as sketched in Figure 1.16a. The freestream Mach number ahead of the wedge is 2.0, and the freestream pressure and density are 1.01 × 10$ N/m² and 1.23 kg/m', respectively (this corresponds to standard sea level conditions). The pressures on the upper and lower surfaces of the wedge are constant with distance s and equal to each other, namely, pu = pi = 1.31 × 10° N/m², as shown in Figure 1.16b. The pressure exerted on the base of the wedge is equal to pœ. As seen in Figure 1.16c, the shear stress varies over both the upper and lower surfaces as r, = 431s-0.2. The chord length, c, of the wedge is 2 m. Calculate the drag coefficient for the wedge. 34.2 Wae ange

Consider the supersonic flow over a 5° half-angle wedge at zero angle of attack, as sketched in Figure 1.16a. The freestream Mach number ahead of the wedge is 2.0, and the freestream pressure and density are 1.01 × 10$ N/m² and 1.23 kg/m', respectively (this corresponds to standard sea level conditions). The pressures on the upper and lower surfaces of the wedge are constant with distance s and equal to each other, namely, pu = pi = 1.31 × 10° N/m², as shown in Figure 1.16b. The pressure exerted on the base of the wedge is equal to pœ. As seen in Figure 1.16c, the shear stress varies over both the upper and lower surfaces as r, = 431s-0.2. The chord length, c, of the wedge is 2 m. Calculate the drag coefficient for the wedge. 34.2 Wae ange

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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Find the A', N', L', D'

Example: supersonic wedge Consider the supersonic flow over a 5° half-angle wedge at zero angle of attack, as sketched in Figure 1.16a. The freestream Mach number ahead of the wedge is 2.0, and the freestream pressure and density are 1.01 x 10° N/m² and 1.23 kg/m', respectively (this corresponds to standard sea level conditions). The pressures on the upper and lower surfaces of the wedge are constant with distance s and equal to each other, namely, p„ = p1 = 1.31 × 10$ N/m², as shown in Figure 1.16b. The pressure exerted on the base of the wedge is equal to Px. As seen in Figure 1.16c, the shear stress varies over both the upper and lower surfaces as t = 431s-0.2. The chord length, c, of the wedge is 2 m. Calculate the drag coefficient for the wedge. 342 Wave angle P-101 x 10'Nim Shock wae P13I x 10'N/ T. (431) () P.123 kgm N/m? Presure Distribution Flow Field Picture Wedge body M. =2 t- 1.01 x 10'Nm? Shear Stress Distribution P=131 x 10' N C2 m (a)
Transcribed Image Text:Example: supersonic wedge Consider the supersonic flow over a 5° half-angle wedge at zero angle of attack, as sketched in Figure 1.16a. The freestream Mach number ahead of the wedge is 2.0, and the freestream pressure and density are 1.01 x 10° N/m² and 1.23 kg/m', respectively (this corresponds to standard sea level conditions). The pressures on the upper and lower surfaces of the wedge are constant with distance s and equal to each other, namely, p„ = p1 = 1.31 × 10$ N/m², as shown in Figure 1.16b. The pressure exerted on the base of the wedge is equal to Px. As seen in Figure 1.16c, the shear stress varies over both the upper and lower surfaces as t = 431s-0.2. The chord length, c, of the wedge is 2 m. Calculate the drag coefficient for the wedge. 342 Wave angle P-101 x 10'Nim Shock wae P13I x 10'N/ T. (431) () P.123 kgm N/m? Presure Distribution Flow Field Picture Wedge body M. =2 t- 1.01 x 10'Nm? Shear Stress Distribution P=131 x 10' N C2 m (a)
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