P7.121 In gliding (unpowered) flight, lift and drag are in equilibrium with the weight. Show, that, with no wind, the craft sinks at an angle tan≈ drag/lift. For a sailplane with m = 200 kg, wing area = 12 m², AR = 12, with an NACA 0009 airfoil, estimate (a) stall speed, (b) minimum gliding angle; (c) the maximum distance it can glide in still air at z = 1200 m. Weight Drag Horizontal

P7.121 In gliding (unpowered) flight, lift and drag are in equilibrium with the weight. Show, that, with no wind, the craft sinks at an angle tan≈ drag/lift. For a sailplane with m = 200 kg, wing area = 12 m², AR = 12, with an NACA 0009 airfoil, estimate (a) stall speed, (b) minimum gliding angle; (c) the maximum distance it can glide in still air at z = 1200 m. Weight Drag Horizontal

Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)

8th Edition

ISBN:9781305387102

Author:Kreith, Frank; Manglik, Raj M.

Publisher:Kreith, Frank; Manglik, Raj M.

Chapter5: Analysis Of Convection Heat Transfer

Section: Chapter Questions

Problem 5.29P: Air at 20C flows at 1 m/s between two parallel flat plates spaced 5 cm apart. Estimate the distance...

See similar textbooks

Similar questions

Air at 1000C flows at an inlet velocity of 2 m/s between two parallel flat plates spaced 1 cm apart. Estimate the distance from the entrance to the point where the boundary layers meet.
Evaluate the Nusselt number for flow over a sphere for the following conditions: D=0.15m,k=0.2W/mK, hc=102W/m2K.
When a sphere falls freely through a homogeneous fluid, it reaches a terminal velocity at which the weight of the sphere is balanced by the buoyant force and the frictional resistance of the fluid. Make a dimensional analysis of this problem and indicate how experimental data for this problem could be correlated. Neglect compressibility effects and the influence of surface roughness.
Engine oil at 100C flows over and parallel to a flat surface at a velocity of 3 m/s. Calculate the thickness of the hydrodynamic boundary layer at a distance 0.3 m from the leading edge of the surface.
Evaluate the dimensionless groups hcD/k,UD/, and cp/k for water, n-butyl alcohol, mercury, hydrogen, air, and saturated steam at a temperature of 100C. Let D=1m,U=1m/sec, and hc=1W/m2K.
5.6 A fluid flows at 5 over a wide, flat plate 15 cm long. For each from the following list, calculate the Reynolds number at the downstream end of the plate. Indicate whether the flow at that point is laminar, transition, or turbulent. Assume all fluids are at 40°C. (a) air, (b) , (c) water, (d) engine oil.
5.4 Evaluate the Stanton number for flow over a tube from the following data: , , , , .
Temperature-measuring instruments may be designed to measure the temperature of vapors, ________, and________.
The drag on an airplane wing in flight is known to be a function of the density of air (), the viscosity of air(), the free-stream velocity (U), a characteristic dimension of the wing (s), and the shear stress on the surface of the wing (s). Show that the dimensionless drag, sU2, can be expressed as a function of the Reynolds number, Us.
A 6-in. diameter hole is drilled in the conical frustum. Calculate the volume and the surface area of the resulting body.
Compute the surface area of the axi-symmetric domed structure.
Repeat Prob. 4.152 assuming that the 400-kN force is applied at O instead of L.