Flight dynamics –II Stability and control Prof. E.G. Tulapurkara Chapter 1 Introduction (Lectures 1‚2 and 3) Keywords : Importance of stability and control analysis ; brief historical background ; basic concepts – static stability‚ dynamic stability‚ longitudinal‚ lateral and directional stability‚ control fixed and control free stability ; controllability; subdivisions of the subject; course outline. Topics 1.1 Opening remarks 1.2 Brief outline of historical developments 1.2.1 Early developments
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Introduction: In any pipe system there is going to be a loss of energy due to the effect of viscosity from a fluid acting upon the surface of the pipe‚ this is called Friction Loss. This type of lost depends on the shear stress due to the walls of the pipe and the fluid. It also depends in weather the fluid is laminar or turbulent. A major difference between these two flows is that due to a viscous layer created in turbulent flow the roughness of the pipe can be taken in account while in laminar
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Figure 1 below shows the change in magnitude of the steady state acceleration with time. This graph complies with Newton’s second law as the force applied is equal to 1 and the mass remains constant so and an acceleration of one is expected. I also tested this by changing the value of the force applied‚ to a value of 2‚ which in theory should give and equivalent change in the acceleration‚ to a value of 2. From Newton’s second law: it can be seen that as the force varies‚ provided moment of inertia
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An investigation to find out whether the mass of an object attached to the bottom of a paper helicopter affects the time it takes to travel a fixed distance Aim: Does the mass of an object affect the time it takes to travel a fixed distance? Introduction: This is an experiment to find out the relationships between mass‚ distance‚ velocity and time. Dependent Variable: The height where the helicopter is dropped from. Independent Variable: The velocity of the helicopter‚ the time it takes for
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11/19/2012 MARE 451 Senior Design Capstone Project 1 Fall 2012 | ------------------------------------------------- Brian Tiefenthaler ------------------------------------------------- Brian Tiefenthaler | MLP’s MARE 451 Sr. Design Tesla Turbine | | MLP’s MARE 451 Sr. Design Tesla Turbine | Table of Contents Duties and responsibilities Page 3 Discussion of Tesla Turbine Page 4 Brian’s Responsibilities Page 7 Drag
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MODEL QUESTION PAPER B.E. Aeronautical Engineering Semester : V AE333 - AIRCRAFT PERFORMANCE Time 3 Hours Answer all the questions PART- A (10 x 2 = 20 Marks) 1. For a bluff body skin friction drag is more than pressure drag. True/ false. Justify your answer. 2. Two identical airfoils are kept in identical flow conditions. The surface of one Airfoil is relatively more rough. This airfoil will have higher stalling angle than the other. True/ False. 3. 4. 5. Justify your answer. Maximum Marks : 100
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ME313L Fluid Mechanic Lab Manual (DRAFT) Pipe Friction Experiment Object: The friction loss in a small-bore horizontal pipe is to be determined over a wide range of Reynolds number. Both laminar and turbulent flow regimes are to be studied. Equipment: Air valve Water manometer Mercury U-tube Isolating tap meter From water supply Needle valve Test tube Figure 1 Pipe friction apparatus A. Laminar Flow The laminar pipe friction apparatus is shown above. It consists of a water loop. The
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This egg drop experiment forced me to think and develop a design that I felt confident with. I developed several models and tested them numerous times‚ but could not settle on one. Eventually‚ I was able to put an addition onto one of my designs which gave me confidence in its ability to protect that precious egg. I will explain why my design worked so well in respect to impulse‚ air resistance‚ and stability. First‚ I will discuss impulse. Impulse is a force acting briefly on a body and producing
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Discussion The results did not give enough accurate data‚ due to the ability of the catapult and the weights used‚ the point at which the projectile stopped being efficient was not evident. If the experiment had been undertaken in more controlled and technology used more efficiently‚ like a robotic catapult‚ than the effect of weight on the motion of a projectile would have become more apparent. Furthermore‚ the reliability of the experiment would be drastically increased due to the use of more
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Pressure Distribution around a Symmetric Aerofoil Abstract: The following report is based on an experiment conducted to calculate the lift curve slope for a symmetrical aerofoil subjected to varying angles of attack. Pressure readings were taken at different points on the upper and lower surface of the aerofoil. The report concludes that maximum lift is generated between 12 º -15º‚ which is also the stall point. It also states that region close to the leading edge contributes most to the lift force
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