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For the below low-speed wind tunnel (Fig. 1), Settling chamber (reservoir) PI A₁ Nozzle V₂ P2. A2 2 Test section Diffuser Figure 2: Low-Speed Wind Tunnel V3 P3 A3 A) Derive a mathematical expression to determine the flow velocity at the test section? B) At the sea level conditions, calculate the velocity at the test section when A₁/A2=10 and the pressure difference is 4.9 kPa?

For the below low-speed wind tunnel (Fig. 1), Settling chamber (reservoir) PI A₁ Nozzle V₂ P2. A2 2 Test section Diffuser Figure 2: Low-Speed Wind Tunnel V3 P3 A3 A) Derive a mathematical expression to determine the flow velocity at the test section? B) At the sea level conditions, calculate the velocity at the test section when A₁/A2=10 and the pressure difference is 4.9 kPa?

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
Problem 1.1MA
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For the below low-speed wind tunnel (Fig. 1), Settling chamber (reservoir) V₁ PI Nozzle V₂ P2. A2 Test section Diffuser Figure 2: Low-Speed Wind Tunnel P3 A3 A) Derive a mathematical expression to determine the flow velocity at the test section? B) At the sea level conditions, calculate the velocity at the test section when A1/A2=10 and the pressure difference is 4.9 kPa? C) What is a critical Reynolds number on an airfoil? D) If the airfoil has a critical Reynolds number of 550,000, how far aft of the airfoil's leading edge will transition occur?
Transcribed Image Text:For the below low-speed wind tunnel (Fig. 1), Settling chamber (reservoir) V₁ PI Nozzle V₂ P2. A2 Test section Diffuser Figure 2: Low-Speed Wind Tunnel P3 A3 A) Derive a mathematical expression to determine the flow velocity at the test section? B) At the sea level conditions, calculate the velocity at the test section when A1/A2=10 and the pressure difference is 4.9 kPa? C) What is a critical Reynolds number on an airfoil? D) If the airfoil has a critical Reynolds number of 550,000, how far aft of the airfoil's leading edge will transition occur?
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