Given: The plane accelerates in its current trajectory with a= 100 m/s^2 Angle theta= 5° W=105 kips F_drag= 80 kips m= 1000 lbs Find: F_thrust, F_lift Please include the KD.
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- The drag equation for the Gofaster 172 is: D = 0.0003v2A. D is drag in pounds; v is airspeed in feet/second; and A is aircraft frontal area in square feet. At maximum airspeed, D = 140 lbs. How much does max airspeed INCREASE if the fuselage is narrowed such that frontal area A is reduced from 16 ft2 to 14 ft2? Give the answer in ft/sec AND mph. drag is 140 lbs. at maximum airspeed, regardless of frontal area. the question is: what is the INCREASE in max airspeed, not what is the max airspeed.The Cessna Citation executive jet weighs 67 kN and has awing area of 32 m2. It cruises at 10 km standard altitudewith a lift coeffi cient of 0.21 and a drag coeffi cient of0.015. Estimate (a) the cruise speed in mi/h and (b) thehorsepower required to maintain cruise velocity.Unless stated otherwise take:Patm = 10^5, P(water) = 1000 kg/m^3 ; P(air) = 1.2 kg/m^3 ; g = 9.8m/s^2gage pressure Pg = P - PatmUnless specified otherwise assume uniform velocity profiles in duct locations.The Bernoulli eq’n (BE), P + ½ρV2 + ρgz = constant In this formulation the scalar variable z is the vertical height measured opposite the direction of g (z is always taken up independent of your coordinate system; pgz is potential energy)This BE is only valid along a streamline in steady state flow, when viscous friction effects can be ignored, called “ideal” fluid motion, and the density is assumed to be constantthe differential radial component of –?P + ρg = ρawith the centripetal acceleration , ar = - V^2/r , to get dp/dr = ρgr + ρV^2/rThe Bernoulli eq’n is often divided through by the constant ρg ≡ γ so that each term has units of length, a height or “head” : (P/ ρg) + (V2/2g) + (z) = constant. Q = VA = flow rate = constant, as a second eq’n to solve for an unknown velocity. the…
- A sea-level automobile tire is initially at 32 lbf/in2 gagepressure and 75 °F. When it is punctured with a hole that resemblesa converging nozzle, its pressure drops to 15 lbf/in2gage in 12 min. Estimate the size of the hole, in thousandthsof an inch. The tire volume is 2.5 ft2.Determine the velocity required for take off for an aircraft with the following characteristics.Aircraft mass: 7200 kgWingspan: 15 mWing shape: rectangularWing chord length: 1.8 mWing airfoil: NACA 4415Wing angle of attack: 7× 0.5 + 5 degreesHint: Check NACA charts for required parameters.A tornado in atmospheric air is simulated by a CCW free vortex as a potential flow field. The velocity measured at r = 1 m from the center is 60 m/s. Determine the magnitude of dynamic pressure P at r = 10 m . (Use pi number = 3 , Air density = 1 .0 kg/m3 )ANSWER: P= 18 Pa
- The cart in Fig. moves at constant velocity V 0 =12 m/s and takes on water with a scoop 80 cm wide that dipsh = 2.5 cm into a pond. Neglect air drag and wheel friction.Estimate the force required to keep the cart moving.In the real flow of air (ρ=1.225 kg/m3) around a cylinder, the circulation is calculated to be 3.97 m2/s. If the free stream velocity is 30m/s, what is the lift generated per meter length of the cylinder? A. 150 N/mB. 160 N/mC. 170 N/mD. 200 N/mA smooth wooden sphere (SG = 0.65) is connected by athin rigid rod to a hinge in a wind tunnel, as in Fig. Air at 20°C and 1 atm flows and levitates the sphere.(a) Plot the angle θ versus sphere diameter d in the range1 cm≤ d≤15 cm. (b) Comment on the feasibility of thisconfiguration. Neglect rod drag.
- IBL, Flat Plate. Apply the integral boundary layer analysis to a flat plate turbulent flow as follows. Assume the turbulent profile u/U = (y/δ)1/6 to compute the momentum flux term on the RHS of IBL, but on the LHS of IBL, use the empirical wall shear stress, adapted from pipe flow: ?w = 0.0233 ⍴U2 (v/Uδ)1/4 where the kinematic viscosity ν = μ/⍴. It is necessary to use this empirical wall shear relation because the turbulent power law velocity profile blows up at the wall and cannot be used to evaluate the wall shear stress. Compute (a) (δ/x) as a function of Rex; (b) total drag coefficient, CD, L as a function of ReL; (c) If ReL = 6 x 107 compare values for this IBL CD,L and those empirical ones given in Table 9.1 for both smooth plate and transitional at Rex = 5 x 105 cases. Note: You must show all the algebra in evaluating the IBL to get full credit. Ans OM: (a) (δ/x) ~ 10-1/(Rex)1/5; (b) CD,L ~ 10-2/(ReL)1/5; (c) CD,IBL ~ 10-3; CD,Smooth ~ 10-3; CD,Trans ~ 10-3Assume that the Flettner rotor ship of Fig. has a waterresistance coefficient of 0.005. How fast will the shipsail in seawater at 20°C in a 20-ft/s wind if the keel alignsitself with the resultant force on the rotors? [Hint: This is aproblem in relative velocities.]You are watching air flow over a smooth flat plate with a width of 5.0 meters. Noticing that the inlet air has a uniform flow with velocity of 10.8 m/s, while downstream a boundary layer is formed with a height of 2 cm. Measuring it, the velocity profile of the boundary layer is u(y) = 10(30y - 100y2) m/s. You imagine a rectangular box around the flow and wonder if mass is crossing the upper boundary (see diagram below). You cant decide if mass is entering or leaving the upper boundary, so you decide to calculate it. How much air is entering/leaving the control volume thru the upper surface?