Fluid Mechanics 3-Aerofoil Lab Report Essay

In conclusion, the purpose of this lab was to decide if the sizes of the paper helicopters would have an effect on their descent times. One theory was that if the size of the paper rotocopter increases, then their descent time will also increase.To determine the results of this experiment certain procedural steps were followed. Firstly all five of the rotocopter were cut out, and folded on the dotted line, the paperclip was used to hold the flaps on the bottom of the

This report shows the effects of weight distribution has on the flight distance of a paper airplane. Just like with real airplanes, paper airplanes rely on aerodynamics to get the airplane to fly, although, they may not look or fly the same they use the same. Changing the postion of where the weight is distrubuted on a paper airplane can affect the planes ability to fly as far.

As a result of the experiment and computation of data, the aerofoil was found to have a critical Mach number of M=0.732. Below this freestream Mach number the Prandtl-Glauert law predicted results very

In this experiment, the velocity profile for a flat plate at zero pressure gradient of a boundary layer at two different stream wise points were acquired. The investigation was also based on and how changes in Reynolds number affect the velocity distribution within boundary layers. Parameters such as the Momentum Thickness, Displacement Thickness, Shape Factor, shear stress and coefficient of friction was also calculated to gain a better understand of boundary layers. The experimental values calculated were compared to the theoretical Blasius for laminar flow and Power Law Solutions for turbulent flow to see how they varied. It was found out the higher the Reynolds number the greater the boundary layer thickness. As the

In this essay, I will explain how the impact of new technology (e.g. aircraft) on methods that were used to fight in the air in WW1 and WW2.

This aerofoil is placed inside a 1.00m by 0.77m test section of an open return low speed wind tunnel, with a contraction ratio of 5.6. This aerofoil is mounted on a turntable, so that the angle of attack to the horizontal can be adjusted. The wind tunnel is used in aerodynamics to research the effects of fluids moving around objects.

World War I was the first conflict in which airplanes were so greatly utilized and played significant roles. The military’s flying machines were first used mostly for reconnaissance, but soon made into offensive weapons (Greatest). Aircrafts were relatively simple and not very maneuverable; but at the same time, anti-aircraft technology was not highly developed. During the years 1914 to 1918, dramatic improvements were made to the structures of airplanes, as well as in control and propulsion systems. Great advancements were being made in the field of aerodynamics (Greatest). World War I required planes to be built for higher speeds, higher altitudes, and greater maneuverability. Aircraft were now being constructed to complete various tasks. The most common types being produced were bombers, fighters, and reconnaissance (Brinkley 689). The major powers were competing for control over the skies, and by countering one another, technology progressed one step at a time.

AIAA has earned an international reputation as the preeminent publisher of cutting-edge aerospace books and journals, and the leading source of aerospace industry archives, dating back to the early 1900s. Over the past eight decades, AIAA and its predecessor organizations have published over 300 books and almost 200,000 technical articles. AIAA’s current publications include seven technical journals, a magazine, three book series, national and international standards documents, a growing number of e-books and other electronic products, and a full-service, interactive Web site. For the most authoritative technical publications, look to

Clark Eldridge, an engineer from Washington State, had designed a trusted, conventional suspension bridge that would cost eleven million dollars. He requested that amount from the Federal Public Works Administration. However, Leon Moisseiff developed a design modification that would make the total cost of building the bridge much less- only eight million dollars. He swapped out the twenty-five feet long sturdy trusses as the form of support for the much cheaper alternative of 8 foot long girders, which were proven to be an insufficient form of support from the collapse of this bridge. His design accounted for an overall thinner bridge; and since his was the cheaper option, it was chosen for construction. However, the width of the bridge in comparison to the length, as well as the absence of trusses which would provide stability, are both part of Moisseiff’s “cost-effective”, yet impractically unsafe design. Since his design was flawed, he is mainly responsible for the bridge collapse. However, the board of engineers who approved his design are also partially responsible for the bridge collapse, as this unsafe design was allowed to be constructed. Meanwhile, it is imperative to remember that theories on aerodynamics were not fully developed as of the time that this bridge was constructed. Therefore, the full effect of oscillating forces was not properly accounted for due to the

Ever since I was little I was amazed at the ability for a machine to fly. I have always wanted to explore ideas of flight and be able to actually fly. I think I may have found my childhood fantasy in the world of aeronautical engineering. The object of my paper is to give me more insight on my future career as an aeronautical engineer. This paper was also to give me ideas of the physics of flight and be to apply those physics of flight to compete in a high school competition.

This project is intended to give the student an improved understanding of aircraft dynamic behavior thought the use of a SIMULINK flight simulation. The student is to use knowledge of flying and handling qualities to appropriately grade a certain maneuver, of a certain aircraft, under a certain condition. The student is to modify the performance of an aircraft through the implementation of a control law.

Since the beginning of recorded history, humans have always had a fascination with flight. Now that we live in a world where boarding an airplane and flying across the country – or even the world - is simply a part of everyday life, the wonder of flight has diminished for many. Despite this, physics students from all around continue to delight in the many physical forces that play a part in keeping these huge objects (like jumbo jets) from falling out of the sky!

A wind tunnel is a key instrument used by Aerospace engineers to accurately measure the aerodynamic forces and moment on an aircraft model. The aerodynamic forces and moments that the model experience then can be compared to the real-life conditions that an aircraft experiences in real-time. An important in tool that allows us to find these different force is the L.A. Comp wind tunnel’s pyramidal balance. This kind of balance allows aerospace engineers to measure all the force: lift, drag, and side force; as well as all the moments: pitching, yawing, and rolling [1]. Figure 1, you are able to see where each of these forces are action and along which axis.

An aerofoil is the structure and main principle behind flight, it works by manipulating air pressure to generate lift for the aircraft. Many things affect the amount of lift produced by a wing such as speed of the aircraft, the density of the air and the

Airfoil is the main part of the airplane which contributes the lift required by the airplane to fly in the air. By varying the wing’s area and the angle of attack, different lift can be created and can