The Newtons Law of Motion - Report Example

1. Inertia, the first of the three Newton’s Law of Motion, d that a body will remain at the same speed and in the same direction unless acted upon by an external force (Headquarters, 2007). 2. Rho or ρ, in physics and chemistry, pertains to the mass per unit volume of a material also known as density. 3. The International Standard Atmosphere (ISA) is a tabulated model of how the pressure, density, viscosity and temperature of the Earth’s atmosphere change as altitude changes. 4. A Newton (N) is a unit of force equivalent to one kilogram of matter multiplied by its acceleration in meters per second squared (kg-m/s2). 5. Maneuverability is the ability to create controlled changes in movement or direction towards an objective. 6. Dynamic Energy concerns the conversion of energy to facilitate motion. 7. Lift Coefficient (CL) is a dimensionless coefficient describing the ratio of the lift pressure to the dynamic pressure in reference to the planform area of the wing or the maximum cross-sectional area of the fuselage. It can be quantified using the equation where ρ is the density of air in slugs per cubic foot, V2 is the airspeed in feet per second and A is the surface area in square feet (Carpenter and Houghton, 2003). Basically, the shape and design of the airfoil and the Angle of Attack determines the coefficient of lift (Headquarters, 2007). 8. Total reaction also known as Total Aerodynamic Force (TAF) (Headquartes, 2007) pertains to the resultant of the aerodynamic forces illustrated below acting on the airfoil of the plane (Carpenter & Houghton, 2003). 9. Aircraft Attitude is the technical term for the aircraft’s orientation relative to its center of mass. 10. The Maximum Lift Coefficient is achieved as the wing operates at maximum lift while flying at minimum flying speed usually at take-off or landing (Talay, 1975). 11. Deployment is the positioning or relocation of any forces and/or material into formation for battle or other desired operational areas (US Dept. of Defense, 2005). 12. Energise basically to provide energy or stimulation to induce work. 13. The types of drag according to Carpenter and Houghton (2003). Type of Drag Causes Effect Reduction Induced Lift Trailing vortex at the tip of the wings Lessen Angle of Attack Form Form of aircraft Turbulence Streamlining Wave High-speed Flight Shock waves Speed limitation Skin-friction Friction on the surface body Shear stress opposing the flow of motion Reduce friction by altering surface area and/or fluid viscosity; or introduction of lubricant; or keeping the plane clean *Parasite Drag=Skin-friction Drag + Form Drag *Total Drag=Parasite Drag + Induced Drag *Pressure Drag=Induced Drag + Wave Drag + Form Drag 14. The Sine Function is not only essential in the computation of resultant forces with respect to the aircraft’s attitude. It is also used in the computation of the Crosswind component (CW) with the equation where A is the angle of the wind relative to the direction of travel and WS is the wind speed. 15. The Cosine Function, also important in the calculation of the summation of forces, is useful in the determination of the tailwind and headwind effects on the flight of the aircraft. 16. The Adverse Yaw is done by rolling the aircraft by the use of ailerons. For example, if an aircraft’s right aileron is down while the left aileron is up, it generates and two opposite lift forces resulting to a left roll (Headquarters, 2007). 17. Trim Controls are the efforts made to keep the flight in a position with constant Angle of Attack and with zero pitching moment (Headquarters, 2007). 18. Frise Ailerons add drag by extending one part of the aileron down into the airstream while the other half of the aileron is extended up into the airstream according the manual prepared by the Headquarters of the Department of Army (2007). 19. A Stabilator is the combination of a stabilizer and an elevator for better maneuverability. It is used to generate and control the pitching motions of the aircraft (Benson, 2008). 20. The speed of the boat can be obtained by measuring the flow of the water beneath it relative to the surface of the boat. This can be done by measuring the static and dynamic pressures of the flow using tubes connected to pressure gauges with openings oriented perpendicular and parallel to the flow respectively (Anderson & Eberhardt, 2001). The changes in dynamic pressure would be directly proportional to the speed of the boat. 21. Tube Effect of Blockage Pitot The dynamic pressure, and in turn also the total pressure, will not be accurately measured. This will result to an incorrect speed reading. Static If there is no change in total pressure, changes in static pressure to compensate for changes in dynamic pressure will not be noted. A false change in speed will be recorded. Both The total pressure reading will be incorrect such that it would be inconclusive if there is any change in air flow. 22. The B747 has a wider wingspan than the common light aircraft to compensate for its heaviness. Its wider wingspan lowers its wing load and effectively slows down its flight. However, its wingspan allows the plane to have better control over the aircraft’s attitude and therefore increases maneuverability. 23. Structural loads are loads or forces acting on the aircraft caused by its own internal structure and form. One example is the weight of the material used in the body of the aircraft for it to be enough to withstand the pressure during flight while also being strong enough to support its cargoes. Structural loads may also pertain to the forces exerted to specific parts of the aircraft due to its form. 24. According to Benson of NASA (2010), lift is generated due to the contact between the air and the flying solid object. Since the molecules of air is free to move, there is variation in both pressure and velocity along the flow of air. Making use of either the Bernoulli’s equation or Newton’s third law of motion, integration of either pressure or velocity variations would conclude an aerodynamic force. The component of this resultant force perpendicular to the original flow of air is the lift generated by the change in pressure and speed. The component along the airflow is considered the drag. 25. *from http://www.hq.nasa.gov/pao/History/SP-468/ch10-5.htm As shown above, the Krueger flap is simpler. The flap, when closed, increases the radius of the leading edge if the wing which reduces the pressure gradient. A separation bubble will be formed underneath the flap which will be released when the flap is extended. It therefore increases camber while also increasing the angle of attack. 26. A trailing-edge flap increases both the camber of the wing and the maximum lift coefficient. Because of this, the lift is moved toward the trailing edge of the wing resulting to a nose-down pitching moment (Carpenter and Houghton, 2003). 27. The Fowler flap when extended can move both rearward and down (Carpenter and Houghton, 2003). It increases camber and wing area which in turn increases maximum lift coefficient. 28. The Fowler flap increases the wing area (Carpenter and Houghton, 2003). 29. At highway speeds, that is, 100 - 110 km/h, a class 8 tractor-trailer uses 53% of the usable energy produced by the vehicle engine to overcome aerodynamic drag, while rolling resistance consumes about 32% of the usable energy. 30. Where the blue arrows show skin-friction drag and the orange arrows are form drags. There is no lift generated such that there is no induced drag. Neither are wave drags which are present only for high-speed flights (Carpenter and Houghton, 2003). For the skin-friction drags, the wheels should be designed appropriately and well-maintained. For the form drags, the edges can be smoothed into curves. The antennas should also be removed unless necessary. The gap between the truck and the trail should be minimized if not eliminated. The surface area of the whole vehicle is suggested to be smooth. 31. *from http://www.av8n.com/how/htm/4forces.html As shown in the figure above, the angle of the plane tilts the lift away from the vertical axis. Assuming that the lift has the same magnitude as the weight before tilted, then the resulting vertical component of the lift would be less than that of the weight. 32. A fin or vertical stabilizer can be attached to the fuselage so that the side of the aircraft would be larger behind the center of gravity. This would increase the area, create a desirable yawing moment and therefore, improves the directional stability. 33. An aircraft cannot fly straight and level if it is in an out-of-trim position. If this happens, it would be difficult to control the attitude of the plane. The gauges and parts of the plane may not function properly. The pilot may also get disoriented and could end up in an accident. 34. At speeds higher than 300 knots, propellers suffer more from compressibility effects and high drags and become less efficient (Reithmaier, 1995). References: Anderson, D. F. & Eberhardt, S. (2001). Understanding Flight. United States of America: McGraw-Hill Companies, Inc. Benson, T. (2008). Stabilator. Glenn Research Center, National Aeronautics and Space Administration. Retrieved from http://www.grc.nasa.gov/WWW/k-12/airplane/stablator.html Benson, T. (2010). Bernoulli and Newton. Glenn Research Center, National Aeronautics and Space Administration. Retrieved from http://www.grc.nasa.gov/WWW/k-12/airplane/bernnew.html Carpenter, P. W. & Houghton, E. L. (2003). Aerodynamics for Engineering Students. (5th ed.). Great Britain: Martins the Printers. Headquarters. (2007). Fundamentals of Flight. Washington, DC: Department of the Army. Lift, Thrust, Weight and Drag. (2005). Retrieved from http://www.av8n.com/how/htm/4forces.html Quest for Performance: The Evolution of Modern Aircraft. Part II: The Jet Age. Chapter 10: Technology of the Jet Airplane. High-Lift Systems. Retrieved from http://www.hq.nasa.gov/pao/History/SP-468/ch10-5.htm Reithmaier, L. (1995). Mach 1 and Beyond: The Illustrated Guide to High-Speed Flight. United States of America: McGraw-Hill Companies, Inc. Talay, T. A. (1975). Introduction to the Aerodynamics of Flight. Washington, DC: Scientific and Technical Information Office, National Aeronautics and Space Administration. US Department of Defense. (2005). Dictionary of Military and Associated Terms. Retrieved from http://www.thefreedictionary.com/deployment Read More