Surface Pressure Measurements on an Aerofoil in Transonic Flow

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 experiment in a low speed flow the static pressure around an aerofoil will be observed and discussed. The lift on the aerofoil will also be calculated and compared with the theoretical value. The aerofoil being used in this particular experiment is symmetrical and is taking place in a wind tunnel with a speed of 18.5m/s, therefore the flow is assumed to be incompressible. The different pressures along the surface of the aerofoil will be measured at an angle of attack of 4.1 degrees and 6.2

The hypothesis of the total experiment is that as the mass of the samara increases, thus increasing the wing loading, the rate of the samara will increase significantly.

The purpose of this lab is to show how the quantity of wings effects the height a 2 oz. bottle rocket launches into the air. The wings have a vital effect on the flight of the rocket. The fins keep the rocket stabilized and going in the right direction. The way that the fins do this is the same way that the feathers on an arrow keep it flying straight. The increased drag on the back end of the fuselage of the rocket, keeps the back end in the back.

Therefore if two spheres have the same Reynold’s number, they should both have the same aerodynamic characteristics even if the spheres are of different sizes and/or are flying at different speeds. The boundary layer is a thin layer of air which lies closely to the surface of the body in motion, and within this layer the adverse pressure gradient is crated which causes the separation of flow. When the Reynolds numbers are low, the boundary is smooth and called laminar. Laminar boundary layers usually reduce drag on most shapes, however due to their fragile nature they separate from the surface of an object very easily when they encounter an adverse pressure gradient, and this separated flow causes the drag to remain so high below the critical

The sound waves that we encounter in our daily lives exist as pressure vibrations in the air, water, and solid mediums that they travel through - dissipating and becoming weaker as the displacement from the initial source increases. As sound is transmitted in the form of a travelling wave, the pressure varies and is dependent on both the displacement and time passed from its emission, according to the following equation:

* The relevance of this experiment is similar to understanding a real airplane. Paper airplane models are derived from an actual plane these days. The design of an airplane has so much to do with distance, hang time, speed, and many other factors. Understanding the models I have chosen to make help me

Abstract-At transonic speeds an aerofoil will have flow accelerate onwards from the leading edge to sonic speeds and produce a shockwave over the surface of its body. One factor that determines the shockwave location is the flow speed. However, the shape of an aerofoil also has an influence. The experiment conducted compared Mach flow over a supercritical aerofoil (flattened upper surface) and a naca0012 aerofoil (symmetrical). Despite discrepancies, the experiment confirmed the aerodynamic performance of a supercritical aerofoil being superior to a conventional aerofoil. A comparison of the graphical distributions demonstrates the more even pressure distribution on a

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

The purpose of our experiment was to find out what nose cone would work the best for our rocket. Our hypothesis was that the ogive nose cone shape would work the best to eliminate drag. To do our experiment we had 5 different nose cones and tested them on a rocket three times each measuring how high the rocket went each time with an altimeter. The nose cone that we found worked the best was the conical nose cone. The ones that were the worst were the blunt and ogive having only a small difference between the average height flown. The conical nose cone was the only nose cone that had any significant difference and was barely one

To look at how the pressure drop changes when the average velocity is altered in a circular pipe and to plot a graph of Friction Factor versus Reynolds

The purpose of the experiment was to measure the effects of water on sound, as the density of the water is gradually increased by adding salt to the water. The experiment is based on the question: “How is sound effected by traveling through water of various densities?” The variables that were tested for were velocity, frequency, wavelength, period and amplitude of the sound. The group wanted to analyze several characteristics of sound to be able to observe multiple patterns that sound follows while it moves through water of increasing density.

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.

Since the first wind tunnel investigations on high speed flow over a stationary airfoil (1918), it was

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