Annotated_Bib_AVIA305

Drop-load (I)This exercise is part of a series of problems aimed at modeling a situation by progressively refining our model to take into account more and more parameters. This progressive approach is very close to what professional scientists do! context We want to lower a suspended load in a controlled way, so that it hits the ground with a speed whose modulus is not too great. To do this, the suspended load (B) is connected by a rope passing through a pulley to another mass (A), which can move on a horizontal surface. To slow down the descent, we added a spring behind the mass (A).   Information The masses of the charges A and B are known.The mass of the rope itself is negligible (very small compared to the loads).The pulley has negligible mass and can rotate without friction.The charge ? is initially stationary and is at a known height h.The surface on which mass A is placed is horizontal.There is no friction between mass A and the surface on which it is placed.The string attached…

Wind tunnel test section km/h Model FD Moving belt Drag balance The aerodynamic drag of a new Volvo FH truck is to be predicted at a speed of 85 km/h at an air temperature of 25°C (p=1.184 kg/m³, u=1.849x10-5kg/m-s). Volvo engineers build a 1/2 scale model of the FH to test in a wind tunnel. The temperature of the wind tunnel is also 25°C. The drag force is measured with a drag balance, and the moving belt is used to simulate the moving ground. Determine how fast the engineers should run the wind tunnel to achieve similarity between the model and the prototype.

Can you help with both please.

I need help with my MATLAB code. There is an error in the following code. The error says my orbitaldynamics function must return a column vector. Can you help me fix it?   mu_earth = 398600.4418; % Earth's gravitational parameter (km^3/s^2) R_earth = 6378.137; % Earth's radius (km) C_d = 0.3; % Drag coefficient (assumed) A = 0.023; % Cross-sectional area of ISS (km^2) m = 420000; % Mass of ISS (kg)       % Initial conditions: position and velocity (ISS state vector) % ISS initial state vector (km and km/s) - sample data state_ISS =[-2.1195e+03, 3.9866e+03, 5.0692e+03, -5.3489, -5.1772, 1.8324];   % Time span for 10 revolutions T_orbit = 2 * pi * sqrt((norm(state_ISS(1:3))^3) / mu_earth); time_span = [0, 10 * T_orbit];     % Step 3: Numerical integration using ODE solver options = odeset('RelTol', 1e-12, 'AbsTol', 1e-12); [t, state] = ode45(@orbitalDynamics, time_span, state_ISS, options);   % Step 4: Plot the results figure; plot3(state(:, 1), state(:, 2), state(:, 3)); xlabel('X…

Problem 3: Aerodynamics Consider a UPS delivery van. Part A Is this vehicle streamlined? (yes/no) Part B Which drag force will be dominant, friction drag or pressure drag, and why? (<25 words) Part C By what percentage does the speed increase from 55 to 75 mph? [%] Centr Part D By what percentage does the drag force increase from 55 to 75 mph? Assume air as given by the ICAO standard atmosphere at an elevation of 5,000 ft. Assume the aerodynamics of the truck can be predicted by a disk with diameter 9.0 ft.

-Sear x dynamics systems questions 1[1 x Week 15-Mechanical (Tutorials x + | C:/Users/40332698/AppData/Local/Packages/microsoft windowscommunicationsapps_8wekyb3d8bbwe/LocalState/Files/SO/145/Attachments/dynamics%... Q - +3 Page view A Read aloud Add textDraw Highlight V Erase ate the 3/104 The car is moving with a speed vo= 105 km/h up the 6-percent grade, and the driver applies the brakes at point A, causing all wheels to skid. The coefficient of kinetic friction for the rain-slicked bogne-road is = 0.60. Determine the stopping distance ed ISAB. Repeat your calculations for the case when the booga car is moving downhill from B to A. the case -8.0 ai noilsi' SA noitisoq de JDT mot gainnige ge = $1 bacilyon A S → vo 6 search 10. $ R F T V 25 % 5 T G B O Ai O A 6 Y H N & 7 U J Fa ★ 8 M 1 K FO 100 9 prt sc F10 O L ) O home P ; B A end F12 { ? + insert } 1 To 6 9°C Cloudy DENG ^ 7

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According to Froude scaling laws, what should the revolutions per minute of the prototype propeller be under dynamically similar conditions? and According to Froude scaling laws, what should the horsepower output of the prototype propeller be under dynamically similar conditions?

Question 5 a) A 1:20 scale model of a surface vessel is used to test the influence of a proposed design on the wave drag. A wave drag of 6.2 lb is measured at a model speed of 8.0 ft/sec. What speed does this correspond to on the prototype, and what wave drag is predicted for the prototype? Neglect viscous effects, and assume the same fluid for model and prototype. b) Discuss the modelling and types of similarities

3. Problem Estimate the frictional resistance Rp for a container ship using the ITTC 1957 model-ship correlation line Equation (2): 0.075 CF [ log,,(Re) – 21 The ship has the following particulars: Full scale ship data length between perpendiculars Lep length in waterline length over wetted surface 195.40 m Lwz Los For the wetted surface S you can use the following formula by Kristensen and Lützen (2012) derived for container ships. 200.35 m 205.65 m breadth B 29.80 m draft T 10.10 m 37085.01 m3 S = 5 + Lw. T 0.995 displacement design speed Again, use the most up-to-date ITTC water properties sheet for density and kinematic viscosity. V 21.00 kn

What is the link between gust spectrum and force spectrum, and what is the link between force spectrum and response spectrum? Please give the related formulas.

L. y X VA A VB PLANE OF CONTACT BY UBC Engineering On an air hockey table, two pucks of identical mass collide in the middle of the rink. Puck A had an initial m velocity vA 1.9? and puck B had an initial velocity vB = 3.2j The plane of contact can be thought of as a line angled 0 = 34° above the x-axis. If the coefficient of 0.5 between the pucks, what are the velocities of the pucks after the impact? || m according to the x-y axis shown. restitution is e =

> | E9 docs.google.com/form تبديل الحساب Questions 7 نقاط Q1/ The power of 6-blade flat blade turbine agitator in a tank is a function of diameter of impeller, number of rotations of the impeller per unit time, viscosity and density of liquid. From a dimensional analysis, obtain a relation between the power and the four variables. 3. صفحة 2 من

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CASIO fx-991ES PLUS ALPHA CALC EGO the car move ? [Ans. NA 16.5 kN, Ng =42.3 kN, the car does not move] %3D 5. A box weighs 150 kg. The coefficient of static friction between the box and the ground is 0.3. Determine if the 80 kg man can pull the box without slipping when the coefficient of static friction between the man's shoes and the ground is 0.4. Hint: analyse block and man separately i.e. draw separate FBDS

1 The following observations are recorded during a test on a four-stroke petro engine, F.C = 25cc of fuel in 10 sec, speed of the engine is 2600 rpm, B.P = 22 kW, Qair 0.00134 m, piston diameter 90 mm, density of the fuel = 0.85gm/cc , compression ratio = 7.5, CV of fuel = 42000KJ/Kg, room temperature = 24 °C %3D = 140mm, stroke length = %3D %3D %3D 2 A six-cylinder 4-stroke cycle petrol engine is to be designed to develop 250 kW of (b.p) at 2200 rpm the stroke / bore ratio is to be 1.3:1. Assuming nm =80% and an indicated mean effective pressure of 9.5 bar, determine the required bore and stroke. If the compression ratio of the engine is to be 7.5 to 1, determine consumption of petrol in kg/h and in kg/bp.hr. Take the ratio of the indicated thermal efficiency of the engine to that of the constant volume air standard cycle as 0.65 and the calorific value of the petrol as; 44770KJ/kg.

The following equation may be used to estimate the take-off ground run for an aircraft: Equation has been attached as an image. Calculate the take-off ground run, from a runway at ISA-SL conditions, for a twin engine aircraft for which the following data may be assumed Aircraft lift-off speed 155 knots Max take-off gross weight 220 tonnes Wing planform area (S) 358 m Wing CL (t/o flaps deployed, a = 0) 1.1 Wing span 53.18 m Oswald efficiency factor, e 0.7 KGE = CD(IGE) / Co(OGE) 0.4 Co sum (fuselage, wing, tailplane and nacelle) 0.015 Co for undercarriage 0.021 Co for flaps at taking-off setting 0.0073 Coefficient of rolling friction, u 0.02 Engine thrust (assumed constant) 310 kN per engine It may be assumed that 1knot = 0.51444 m/s   It may be assumed that 1knot = 0.51444 m/s

Question 5 a) A 1:20 scale model of a surface vessel is used to test the influence of a proposed design on the wave drag. A wave drag of 6.2 lb is measured at a model speed of 8.0 ft/sec. What speed does this correspond to on the prototype, and what wave drag is predicted for the prototype? Neglect viscous effects, and assume the same fluid for model and prototype.

Sole the part 1 for me just part 1

(b) A wind-tunnel experiment is performed on a small 1:5 linear-scale model of a car, in order to assess the drag force F on a new full-size car design. A dimensionless "drag coefficient" Ca is defined by C, =- pu'A where A is the maximum cross-sectional area of the car in the flow. With the model car, a force of 3 N was recorded at a flow velocity u of 6 m s. Assuming that flow conditions are comparable (i.e., at the same Reynolds number), calculate the expected drag force for the full-sized car when the flow velocity past it is 31 m s (equivalent to 70 miles per hour). [The density of air p= 1.2 kg m.]

(Review experimental scaling) A lightweight parachute is being designed for military use. Its diameter D is 20 ft and the total weight W of the falling payload, parachute, and equipment is 190 lb. The design terminal settling speed V. (or terminal velocity) of the parachute at this weight is 16 ft/s. A one-twelfth scale model of the parachute is tested in a wind tunnel. The wind tunnel temperature and pressure are the same as those of the prototype, which is 70 °F and standard atmospheric pressure. a) Calculate the drag coefficient of the prototype. (Hint: At terminal velocity, speed is constant so weight is in equilibrium with aerodynamic drag.) b) At what speed should the wind tunnel be run in order to achieve dynamic similarity? c) Find the aerodynamic drag force of the model parachute in the wind tunnel in pounds. Payload

The drag force of a new sports car is to be predicted at a speed of 65 mi/h at an air temperature of 25 C. Automotive engineers build a 0.333333333333333 scale model of the car to test in a wind tunnel. The temperature of the wind tunnel air is also 25 C. Determine how fast (in mi/h) the engineers should run the wind tunnel to achieve similarity between the model and the prototype.

What is the major difference between spacecraft orbital mechanics and spacecraft attitude dynamics? (support your answer with examples and mathematical formulas) Please don't copy from internet or chegg NEED DETAILED AND STEP BY STEP ANSWER Short or incomplete answer = thumbs down

Pierce (1948) mechanically measured the frequency (the number of wing vibrations per second) of chirps (or pulses of sound) made by a striped ground cricket, at various ground temperatures. Since crickets are ectotherms (cold-blooded), the rate of their philosophical processes and their overall metabolism are influenced by temperature. Consequently, there is a reason to believe that temperature would have a profound affect on aspects of their behavior, such as chirp frequency. In general, it was found that crickets did not sing at temperatures colder than 60°F or warmer than 100°F. In the following data let X= chirps/sec for the striped ground cricket and Y= temperature in degrees of Fahrenheit.  X   19      19.8        18.4     17.1     15.5    14.7     17.1    15.4    16.2    15   17.2    16     17     14.4 Y    71.6     93.3    84.3    80.6     75.2    69.7    82     69.4    83.3     79.6    82.6     80.6     83.5    76.3 a. use two decimal places: Y bar =? b. use two decimal…

A model pump has an impeller diameter of 30 cm. During a manufacturer's test, this model achieved an efficiency of 80%. A prototype in the same family (geometrically similar) is 10 times larger than this tested model. Under the same operating conditions dynamically similar to those in the model test, what most approximately will be the efficiency of the prototype pump? O 74% OOOO O 64% O 84% O 94%

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While using the Buckingham pi theorem to obtain non-dimensional groups, the repeated variables are chosen to be density, length and velocity and the non-repeat variable is angualr velocity. What is the non dimensional group that will be found in the form of : Non dimensional group= angular velocity x density ______x length ______x velcoity ________

Question 3 The aerodynamic derivative X, may be determined from the following expression: X -pU SCD %3D where p is the air density, S is the wing area, U is the airspeed, and Cp is the drag coefficient. Consider an aircraft of weight 68 kN and wing area 43 m?, flying straight and level under international standard atmosphere (ISA) conditions, where p 1.018 kg/m, at an airspeed of 155 m/s. The aircraft %3D has a drag polar Cp = 0.011 + where Ci is the lift coefficient. Calculate the value of X, at this flight condition. Give your answer in units of Ns/m.

4. Find the width of the belt, necessary to transmit 7.5 kW to a pulley 300 mm diameter, if the pulley makes 1600 r.p.m and the coefficient of friction between the belt and the pulley is 0.22. Assume the angle of contact as 210° and the maximum tension in the belt is not to exceed 8 N/mm width. [Ans. 67.4 mm]