3. Suppose the drag force on a truck is given by the equation: F = cqv² + c2v where c = 4.80 N and cz = 111.8 . Check that this relationship is plausible. Do the units work out? (a) Calculate the required propulsive power at a speed of 55 mi/hr. Express your final answer in Hp. Recall that 1Hp = 745.7 W. (b) Calculate the required propulsive power at a speed of 80 mi/hr. (c) Is the ratio of required powers proportional to the ratio of given speeds? Surprised? Or not?

3. Suppose the drag force on a truck is given by the equation: F = cqv² + c2v where c = 4.80 N and cz = 111.8 . Check that this relationship is plausible. Do the units work out? (a) Calculate the required propulsive power at a speed of 55 mi/hr. Express your final answer in Hp. Recall that 1Hp = 745.7 W. (b) Calculate the required propulsive power at a speed of 80 mi/hr. (c) Is the ratio of required powers proportional to the ratio of given speeds? Surprised? Or not?

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

See similar textbooks

Similar questions

2/A- Airbus 320 fly in steady level flight with altitude 10.5 km and the density at this level p=0.3877 kg/m³, mass of aircraft 6500 kg, wing area 124 m², CD = 0.015+ 0.02 CL², maximum thrust at sea level 53.015 kN. Calculate maximum velocity. C00
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.
Suppose you are designing the propeller of a radio-controlled model airplane. The overall diameter of the propeller is 34.0 cm, and the hub assembly diameter is 5.5 cm. The propeller rotates at 1700 rpm, and the airfoil chosen for the propeller cross section achieves its maximum efficiency at an angle of attack of 14°. When the airplane flies at 30 mi/h (13.4 m/s), calculate the blade pitch angle from the root to the tip of the blade such that ? = 14° everywhere along the propeller blade.
INTERNAL COMBUSTION ENGINESplease write clearly
Give me proper explanation please
Complete proper solution and units. ( You can choose from the choices ) Aerodynamics - Thank you!
The lift on a spinning circular cylinder, in a freestream with a velocity of 10m/s, is measured as L, at standard sea level conditions and L, at an altitude of 10,000ft. (Assume that both cases generate the same circulation around the cylinder.) How do you compare L, and L2? Please choose one of the following alternatives: (1) L1 = L2 (ii) L1 > L2 (iii) L1 < L2 (iv) None of them O i O i O i O iv
An airplane builder wants to build a scaled-down model of a real airplane in a 12:1 ratio in order to be able to perform tests in a wind tunnel. The real plane flies at 126 km/h, while the air speed in the tunnel where the model is located is given by V. The performances of the two will be equivalent for a value of V, in m/s, equal to Data: air viscosity η = 1.8 × 10-5 kg/(m.s) air density ρ = 1.3 kg/m3
At what speed would these fans operate to develop 130 mm water gage when the temperature is 316 deg C? The fans of a certain manufacturer are rated at 152 mm water gage pressure for 10 cubic meters of air per second at 21 deg C, 1200 rpm, and 69% static efficiency
A small model water turbine is tested in a flume where Cp is measured to be 0.38. Assuming dynamic similarity exists, calculate the power output of a full-size turbine of diameter 12 m operating in a tidal stream, where the water density is 1030 kg/m³, μ = 1.307-³ Ns/m² and maximum water velocity of 2.2 m/s.
2. The table below shows experimental data for the shape and pressure distribution on the upper and lower surface of an airfoil at zero angle of attack. X 0 0.25 0.5 0.75 1 Yu 0 0.0952 0.0922 0.0588 0 Fx = dYu dx 5 Y₁ 0 -0.0254 -0.0144 -0.0052 0 PL Pd) d: dx Y = Yu (x) Calculate the drag and lift force on the airfoil by numerically evaluating the integrals = S₁² ( P₂₁ = ['(P₁ - F (P₁ - Pu)dx 0 y = Y₂ (x) Pu 1.000 -1.640 -0.786 -0.212 0 Fy x Pi 1.000 0.589 0.426 0.322 0 Use finite difference approximations of the derivatives and the composite Simpson's rule to evaluate the integrals. Hint: Use central differences to estimate the derivatives wherever possible since they are more accurate than forward or backward differences.
The Antonov An-225 is the heaviest aircraft ever built, with a maximum takeoff weight of 640 metric tonnes. It also has the largest wingspan of any aircraft in operational service. Sea level standard day (sls) conditions for calculations are 15°C; 101.3kPa Rotate speed (Vr) at takeoff (sls): Vr = 154 kts = 1.2×Vmin (1 kt = 0.514 m/s) Cruise Engine Thrust : a) Calculate the lift coefficient for a standard day takeoff b) Calculate the drag coefficient at cruis Fcruise = 0.85 Fmax Engine maximum thrust: Factual,max = Fsls,max×δ θ½ δ = Pactual/Pref; and θ = Tref/Tactual