Airfoils - Revision history

U2berggeist at 20:46, 18 August 2020

2020-08-18T20:46:21Z

U2berggeist: /* Chord */

2020-08-18T20:06:12Z

Chord

U2berggeist: Remove erroneous statement. I'm not sure what the sentence is supposed to mean and can't figure out an appropriate interpretation.

2020-08-18T20:04:45Z

Remove erroneous statement. I'm not sure what the sentence is supposed to mean and can't figure out an appropriate interpretation.

U2berggeist: Improved formatting

2020-08-18T20:03:09Z

Improved formatting

U2berggeist: /* Airfoil Selection */

2020-08-18T19:49:43Z

Airfoil Selection

Get KAS at 13:40, 23 May 2020

2020-05-23T13:40:58Z

Crsntrpk at 02:56, 19 May 2020

2020-05-19T02:56:32Z

Crsntrpk: /* Endplates */

2020-05-18T22:08:19Z

Endplates

Crsntrpk: /* Endplates */

2020-05-18T22:07:52Z

Endplates

Crsntrpk: /* Parts of an Airfoil */

2020-05-18T21:53:54Z

Parts of an Airfoil

@@ Line 6: / Line 6: @@
 ===Chord===
 The chord of an airfoil is the distance from leading edge to trailing edge. It is measured by drawing a straight line from the LE to TE. The chord line often serves as the reference datum for airfoils defined by coordinates.
 ===Camber===
 The camber of an airfoil measures its shape. The camber line is drawn from the leading edge to the trailing edge, staying equidistant from the top and bottom surfaces of the airfoil at each point. The camber at each point is thus the distance from the camber line to either the top or bottom surface of the airfoil. For a symmetric airfoil, the camber line and the chord line are the same.
@@ Line 13: / Line 12: @@
-Airfoils can be compared by different key parameters such as <math>C_l</math>, <math>C_d</math>, <math>C_m</math> and the change of these parameters over the angle of attack. To compare an airfoil, the Reynolds number gives an insight on the ratio of chord length to airspeed (simplified). The Reynolds number is given as:<br /><br /><math display>Re = \frac{\rho u_\infty C}{\mu} = \frac{u_\infty C}{\nu}</math><br />, where <math>C</math> is the chord length, <math>\nu</math> is the kinematic viscosity, and <math>u_\infty</math> is the free stream velocity. To check the Reynolds number on your design visit [http://airfoiltools.com/calculator/reynoldsnumber airfoiltools Reynolds number calculator].
+Airfoils can be compared by different key parameters such as <math>C_l</math>, <math>C_d</math>, <math>C_m</math> and the change of these parameters over the angle of attack. To compare an airfoil, the Reynolds number gives an insight on the ratio of chord length to airspeed (simplified). The Reynolds number is given as:<br /><br /><math display="block">Re = \frac{\rho u_\infty C}{\mu} = \frac{u_\infty C}{\nu}</math><br />, where <math>C</math> is the chord length, <math>\nu</math> is the kinematic viscosity, and <math>u_\infty</math> is the free stream velocity. To check the Reynolds number on your design visit [http://airfoiltools.com/calculator/reynoldsnumber airfoiltools Reynolds number calculator].
 ==Additional Parts==
 ===Endplates===

@@ Line 5: / Line 5: @@
 The trailing edge is the furthest rearward edge of the airfoil.
 ===Chord===
-The chord of an airfoil is the distance from leading edge to trailing edge. It is measured by drawing a straight line from the LE to TE.
+The chord of an airfoil is the distance from leading edge to trailing edge. It is measured by drawing a straight line from the LE to TE. The chord line often serves as the reference datum for airfoils defined by coordinates.
 ===Camber===
 The camber of an airfoil measures its shape. The camber line is drawn from the leading edge to the trailing edge, staying equidistant from the top and bottom surfaces of the airfoil at each point. The camber at each point is thus the distance from the camber line to either the top or bottom surface of the airfoil. For a symmetric airfoil, the camber line and the chord line are the same.

@@ Line 12: / Line 12: @@
-Airfoils can be compared by different key parameters such as <math>C_l</math>, <math>C_d</math>, <math>C_m</math> and the change of these parameters over the angle of attack. To compare an airfoil, the Reynolds number gives an insight on the ratio of chord length to airspeed (simplified). The Reynolds number is given as:<br /><br /><math display>Re = \frac{\rho u_\infty C}{\mu} = \frac{u_\infty C}{\nu}</math><br />, where <math>C</math> is the chord length, <math>\nu</math> is the kinematic viscosity, and <math>u_\infty</math> is the free stream velocity. Two airfoils with the same Reynolds number perform similar. To check the Reynolds number on your design visit [http://airfoiltools.com/calculator/reynoldsnumber airfoiltools Reynolds number calculator].
+Airfoils can be compared by different key parameters such as <math>C_l</math>, <math>C_d</math>, <math>C_m</math> and the change of these parameters over the angle of attack. To compare an airfoil, the Reynolds number gives an insight on the ratio of chord length to airspeed (simplified). The Reynolds number is given as:<br /><br /><math display>Re = \frac{\rho u_\infty C}{\mu} = \frac{u_\infty C}{\nu}</math><br />, where <math>C</math> is the chord length, <math>\nu</math> is the kinematic viscosity, and <math>u_\infty</math> is the free stream velocity. To check the Reynolds number on your design visit [http://airfoiltools.com/calculator/reynoldsnumber airfoiltools Reynolds number calculator].
 ==Additional Parts==
 ===Endplates===

@@ Line 9: / Line 9: @@
 The camber of an airfoil measures its shape. The camber line is drawn from the leading edge to the trailing edge, staying equidistant from the top and bottom surfaces of the airfoil at each point. The camber at each point is thus the distance from the camber line to either the top or bottom surface of the airfoil. For a symmetric airfoil, the camber line and the chord line are the same.
 ==Airfoil Selection==
-Airfoils are available in various shapes and forms and the right arifoil may not even exist for your application. To get an understanding of the variety of arifoils you should check databases such as [http://airfoiltools.com/search/index airfoiltools].
+Airfoils are available in various shapes and forms and the right airfoil may not even exist for your application. To get an understanding of the variety of airfoils you should check databases such as [http://airfoiltools.com/search/index airfoiltools].
-Airfoils can be compared by different key parameters such as Cl, Cd, Cm and the change of these parameters over the angle of attack. To compare an airfoil, the Reynolds number gives an insight on the ratio of chord length to airspeed (simplified). Two airfoils with the same Reynolds number perform similar. To check the Reynolds number on your design visit [http://airfoiltools.com/calculator/reynoldsnumber airfoiltools Reynolds number calculator]. For manual calculation use the formula Re = (fluid density * free stream velocity * chord length) / dynamic viscosity of the fluid.
+Airfoils can be compared by different key parameters such as <math>C_l</math>, <math>C_d</math>, <math>C_m</math> and the change of these parameters over the angle of attack. To compare an airfoil, the Reynolds number gives an insight on the ratio of chord length to airspeed (simplified). The Reynolds number is given as:<br /><br /><math display>Re = \frac{\rho u_\infty C}{\mu} = \frac{u_\infty C}{\nu}</math><br />, where <math>C</math> is the chord length, <math>\nu</math> is the kinematic viscosity, and <math>u_\infty</math> is the free stream velocity. Two airfoils with the same Reynolds number perform similar. To check the Reynolds number on your design visit [http://airfoiltools.com/calculator/reynoldsnumber airfoiltools Reynolds number calculator].
 ==Additional Parts==

@@ Line 12: / Line 12: @@
-Airfoils can be compared by different key parameters such as Cl, Cd, Cm and the change of these parameters over the angle of attack. To compare an airfoil, the Reynoldsnumber gives an insight on the ratio of chord length to airspeed (simplified). Two airfoils with the same Reynolds number perform similar. To check the Reynoldsnumber on your design visit [http://airfoiltools.com/calculator/reynoldsnumber airfoiltoos Reynolds number calculator]. For manual calculation use the formula Re = (fluid density * kinetic viscosity of the fluid * chord length) / dynamic viscosity of the fluid.
+Airfoils can be compared by different key parameters such as Cl, Cd, Cm and the change of these parameters over the angle of attack. To compare an airfoil, the Reynolds number gives an insight on the ratio of chord length to airspeed (simplified). Two airfoils with the same Reynolds number perform similar. To check the Reynolds number on your design visit [http://airfoiltools.com/calculator/reynoldsnumber airfoiltools Reynolds number calculator]. For manual calculation use the formula Re = (fluid density * free stream velocity * chord length) / dynamic viscosity of the fluid.
 ==Additional Parts==
 ===Endplates===

← Older revision		Revision as of 22:08, 18 May 2020
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−	For our vehicles, we cannot extend our wings outside of our wheels, and thus need to find a different solution to limit our induced drag.	+	For our vehicles, we cannot extend our wings outside of our wheels, and thus need to find a different solution to limit our induced drag. Adding endplates physically prevents the high pressure and low pressure region from interacting, thereby reducing the drag generated from this effect. Sadly, endplates can generate their own drag through similar effects. The high pressure ambient air can "spill over" into the low pressure region captured inside the endplates, creating vortices and drag.
−
−
−	Adding endplates physically prevents the high pressure and low pressure region from interacting, thereby reducing the drag generated from this effect. Sadly, endplates can generate their own drag through similar effects. The high pressure ambient air can "spill over" into the low pressure region captured inside the endplates, creating vortices and drag.

@@ Line 11: / Line 11: @@
 ==Additional Parts==
 ===Endplates===
-Endplates
+In a standard wing with no endplates, the wing experiences induced drag due to the high pressure region above the wing coming around the edge to the low pressure region below the wing. This creates vortices and adds extra drag to the vehicle. In a plane, the aspect ratio of the wing can be increased to limit this effect (think about a glider, they frequently have really long wings with a short chord, increasing wing span while limiting wing area).
 ===Supports===
 When designing supports, it is important to take into account deflection and adjustablity