4/30/2024 0 Comments Nacca airfoil databaseReynolds – The Reynolds Number, estimated as the product of the wing chord in feet, times the airspeed in feet per second times 6,369.Īspect Ratio – The ratio of the wing span to its average chord. Aspect ratio has a strong effect on aerodynamic properties of wings. Location – the location of the maximum camber point along the chord, expressed as a percent of the chord. Max Camber – the maximum separation between the chord line and the mean thickness curve, the height of the highest point on the arc, expressed as a percent of the chord. You can click on this link Small Airfoil Data to download the original Open Office file. You can copy, save and print the picture, or double click to enlarge. This table contains the results of that collecting. Over the years I have gathered what I could find. There is very little wind tunnel data to guide us in the selection and use of airfoils for our little models. Most full scale aircraft have thick airfoil sections. Our airfoils are usually thin arcs or flat plates. There is a vast quantity of aerodynamic data published, but most of it is for full scale aircraft with Reynolds Numbers in the millions.Īerodynamic properties also depend on the shape of the airfoil cross section. The Cloud Tramp, with a wing chord of 3″ and a flight speed of around 10 feet per second, has a Reynolds Number of about 16,000. The 6,369 assumes certain values of air density and viscosity that are taken as standard. For our purposes, Reynolds Number is the product of wing chord, in feet, times the airspeed, in feet per second, times 6,369. Aerodynamic scale is quantified as the Reynolds Number. ![]() Aerodynamic scale of airfoils is dependent on the wing chord and the air speed. There are several aerodynamic regimes with different phenomena, such as viscosity, inertia, turbulence or compressability, predominating in each. The values of these coefficients vary with aerodynamic scale. The data may be presented in tables or in graphs. Lift to drag ratio and power factor are calculated at each angle. Lift coefficient, drag coefficient and moment coefficient are measured over a range of attack angles. The aerodynamic properties of airfoils are measured in wind tunnels.
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