sysprob1a - x = 2 5 5 10 20 30 in along centerline(using hand-held pitot probe 2 For α = 10 ◦ Approximate locations where a Δ p is a maximum(note

Fluids Lab 1 (SPL1) – Assignment Wind Tunnel Pitot Measurements Learning Objectives – Practice using pitot probe relations (Bernoulli, etc) – Familiarization with tunnel test procedures – Practice nondimensionalization of data Experimental Rig Test Article: 47:1 Boeing Blended Wing Body (BWB) in Wright Brothers Wind Tunnel Instrumentation: – Tunnel’s pitot-static probe. Reports p o ∞ − p ∞ in Torr (mm Hg). – Hand-held pitot-static probe. Reports p − p ∞ in 10 × Torr. ( p − p ∞ reading must be multiplied by 0.1 to get Torr) Test Conditions Nominal tunnel speed: 40 mph Angles of attack α = 0 ◦ , 10 ◦ Raw Data Acquired 1) For each angle of attack α . . . p o ∞ − p ∞ ≡ q ∞ (from tunnel’s pitot-static probe) p ( x ) − p ∞ ≡ Δ p ( x ) for

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Unformatted text preview: x = 2 . 5 , 5 , 10 , 20 , 30 in along centerline (using hand-held pitot probe) 2) For α = 10 ◦ . . . Approximate locations where a) Δ p is a maximum (note the value) b) Δ p is a minimum (note the value) Normalized Data Presented 1) Top and bottom centerline C p vs x/c o for α = 0 ◦ , 10 ◦ . (both curves on one plot). Model’s centerline chord is c o = 37 . 7 in. 2) Locations of maximum and minimum Δ p , indicated with dots on the BWB outline drawing provided. Also determine the local normalized velocity V/V ∞ at these two locations. Note: Submit only the 2-sided turn-in sheet provided. If the plot is clearly incorrect, partial credit can be given only if you show your work (equations used, sample calculations, etc)....
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