![]() ![]() The information contained herein is property of APR Performance, and may not be reproduced in whole or in part without prior written consent from APR Performance. The Adams CA-2 is a single seat, low -wing, American ultralight aircraft that was designed by Frank Griffith of Corning Aircraft around 1992 and was available as plans for amateur construction until 1999. The following image illustrates both the pressure distribution on the underside of the airfoil The following image illustrates both the pressure distribution and streamlines associated with the airfoil. The following image illustrates the pressure distributions across the surfaces of the airfoil. The following graph illustrates the lift and Drag Coefficient Ratio. The higher the air speed and AOA are, the higher the resultant drag is. The following graph illustrates the effects that air speed and AOA have on drag only. The higher the air speed and AOA are, the higher the resultant downforce is. ![]() The following graph illustrates the effects that air speed and AOA have on downforce only. This reference plane can be simulated by placing a ruler across the top of the center section of an actual airfoil. The Colditz Glider Airfoil Aerodynamics What causes lift. #WING AIRFOIL FREE#At 0 degrees AOA, the reference plane is parallel to the direction of the free air stream (the stream would travel from right-to-left in this image). This diagram showing the cross section of a wing does not fully illustrate how a wing produces lift. The following image illustrates where and how the AOA is referenced. The numbers in the table are represented in Pounds. Greater lift is achieve by curving the wings. The effect achieved by this type of design of a wing is to maintain the laminar flow of air throughout a greater percentage of the chord of. (B) Airplane and bird wings are typically thick airfoils held parallel to the airstream, so as to maximize speed. The following table shows the actual data that were collected from the CFD analysis. The major and most important difference between the two types of airfoil is this, the thickest part of a laminar wing occurs at 50 chord while in the conventional design the thickest part is at 25 chord. #WING AIRFOIL HOW TO#To learn how to interpret and apply this type of CFD data, see sample analysis on the GTC-300 page. This data will provide insight with regards to how and how much the airfoil performs with respect to these conditions. ![]() This data illustrates how the airfoil performs in different conditions by comparing Downforce vs. Saving Earth Britannica Presents Earth’s To-Do List for the 21st Century.Contained herein are the data and results of the Computational Fluid Dynamics (CFD) analysis that was conducted on the GTC-500 airfoil.Britannica Beyond We’ve created a new place where questions are at the center of learning. ![]()
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