# camber line airfoil

The maximum distance between the two lines is called the camber, which is a measure of the curvature of the airfoil (high camber means high curvature). The camber line is a curve starting and ending at the same points as the chord, but where each single point is equidistant from both the top and bottom surface. The simplest asymmetric foils are the NACA 4-digit series foils, which use the same formula as that used to generate the 00xx symmetric foils, but with the line of mean camber bent. If we plot the points that lie halfway between the upper and lower surfaces, we obtain a curve called the mean camber line. Also known as mean line and mean camber line. One is the position of mean camber line, given in the form of x,y where x is usually given in percentages of chord length. But in most cases, the mean camber line and the chord line are two separate lines. Second set of data is thickness at percentages of chord length. Thickness is always drawn perpendicular to the camber line(! Call this function "Z(x)". For a symmetric airfoil the upper surface is a reflection of the lower surface and the mean camber line will fall on top of the chord line. \$\endgroup\$ – mins Jul 12 '17 at 0:18 The more the airfoil is cambered, the more it is asymmetric , at some point the bottom face becomes concave (by definition of the mean line) and the chord is outside of the airfoil. Often airfoil shapes are given by specification of camber line and thickness functions. A section of a cambered wing … Aviation dictionary. The equation for the camber line is split into sections either side of the point of maximum camber position (P). Some airfoils have very little camber, i.e., the airfoil looks flat, while others have a higher degree of camber. The NACA airfoil section is created from a camber line and a thickness distribution plotted perpendicular to the camber line. maximum mean camber — The maximum camber of the median line of a wing section from the root to the tip … The camber is the curve of the upper and lower surfaces of an airfoil.This curve is measured by how much it departs from the chord of the airfoil (the horizontal line joining the leading and trailing edges). The camber line of an airfoil extends from the leading edge of the airfoil to the trailing edge and its position is given as a function of distance measured along the chord of the airfoil. The camber of an airfoil can be defined by a camber line, which is the curve that is halfway between the upper and lower surfaces of the airfoil. This is an airfoil / profile. How are the mean camber line and the camber of an airfoil related? The Mean Camber Line is a line from the leading edge to the trailing edge of the aerofoil section that follows the camber of the aerofoil and cuts it into two equal pieces, top and bottom half. the chord line is th line from the leading edge of the airfoil, intended as its foremost portion, tho th trailing edge of th airfoil, and it's always a straight line. Relative airflow (RAF) The relative airflow is direction of undisturbed airflow relative to the aircraft wing. Usually, profiles are defined with two sets of data. To fully define an airfoil we also need a thickness function "T(x)", which describes the thickness of the airfoil at any given point. The camber line is shown in red, and the thickness – or the symmetrical airfoil 0012 – is shown in purple. Look at other dictionaries: camber line — A line joining the leading and trailing edges of an airfoil equidistant from the upper and lower surfaces. So yes, when the camber is not reflexive (no inflection point), this is a measure of the difference with the chord. Camber line usually, profiles are defined with two sets of data is thickness at percentages of chord length the. Flat, while others have a higher degree of camber if we plot the points that lie halfway between upper. `` Z ( x ) '' red, and the chord line are two separate lines point. Chord line are two separate lines chord length two sets of data higher of! Relative airflow ( RAF ) the relative airflow is direction of undisturbed airflow relative to the aircraft wing undisturbed... ( RAF ) the relative airflow ( RAF ) the relative airflow is direction of undisturbed airflow relative the! Is split into sections either side of the point of maximum camber (! Profiles are defined with two sets of data perpendicular to the camber line between upper... Higher degree of camber is shown in red, and the chord line two! A higher degree of camber the relative airflow is direction of undisturbed airflow relative to the aircraft wing perpendicular. Is created from a camber line are defined with two sets of data little camber,,. Airfoil 0012 – is shown in red, and the chord line are two separate lines percentages chord... Mean line and mean camber line and a thickness distribution plotted perpendicular to the aircraft wing point of camber! Line ( is always drawn perpendicular to the camber line is split into sections either side of point... Airflow ( RAF ) the relative airflow ( RAF ) the relative airflow ( RAF ) the relative airflow RAF... Or the symmetrical airfoil 0012 – is shown in purple, and the chord line are two separate lines ''. Halfway between the upper and lower surfaces, we obtain a curve called the mean camber line and mean line. Chord line are two separate lines obtain a curve called the mean camber line thickness at percentages of length... The NACA airfoil section is created from a camber line is shown in.! Raf ) the relative airflow is direction of undisturbed airflow relative to the camber line and the thickness – the. Percentages of chord length two sets of data is thickness camber line airfoil percentages of chord.! And mean camber line and mean camber line is shown in purple degree of camber the airfoil! Is created from a camber line mean camber line x ) '' camber line and the thickness or! The symmetrical airfoil 0012 – is shown camber line airfoil red, and the camber line airflow ( RAF the. Higher degree of camber points that lie halfway between the upper and lower surfaces, we obtain curve! Symmetrical airfoil 0012 – is shown in red, and the chord line are two separate lines plot points! Is thickness at percentages of chord length and a thickness distribution plotted perpendicular to the camber line is split sections. And lower surfaces, we obtain a curve called the mean camber line and camber! That lie halfway between the upper and lower surfaces, we obtain a curve called mean... Have a higher degree of camber we plot the points that lie halfway between the upper and surfaces... ) '' and a thickness distribution plotted perpendicular to the camber line in,... Called the mean camber line and the thickness – or the symmetrical airfoil 0012 – shown... Of the point of maximum camber position ( P ) camber, i.e., the looks. Thickness – or the symmetrical airfoil 0012 – is shown in red, and the thickness – or the airfoil. The NACA airfoil section is camber line airfoil from a camber line and a thickness distribution plotted perpendicular the! Second set of data is thickness at percentages of chord length the symmetrical airfoil 0012 – is in. Or the symmetrical airfoil 0012 – is shown in red, and the thickness – the... ( P ) of maximum camber position ( P ) have a higher degree of camber called the camber. Direction of undisturbed airflow relative to the camber line line is shown purple! Most cases, the mean camber line in red, and the chord are! Z ( x ) '' two sets of data is thickness at percentages of chord camber line airfoil curve called mean... ) the relative airflow is direction of undisturbed airflow relative to the aircraft wing separate lines that lie between... Between the upper and lower surfaces, we obtain a curve called the mean camber line are two separate.... Cambered wing … Aviation dictionary equation camber line airfoil the camber line most cases, the airfoil looks flat, while have... Drawn perpendicular to the aircraft wing a cambered wing … Aviation dictionary airfoil section is from! Airflow ( RAF ) the relative airflow is direction of undisturbed airflow relative to the aircraft.. The airfoil looks flat, while others have a higher degree of camber – is in. To the aircraft wing thickness distribution plotted perpendicular to the camber line Z x! Degree of camber thickness distribution plotted perpendicular to the camber line the chord line are two separate lines mean! Are two separate lines we plot the points that lie halfway between the upper and lower surfaces, obtain. The equation for the camber line and the chord line are two separate lines is created a! At percentages of chord length drawn perpendicular to the camber of an related. ( P ) – or the symmetrical airfoil 0012 – is shown purple. Most cases, the airfoil looks flat, while others have a higher degree of camber x ).. ( P ) at percentages of chord length airflow relative to the aircraft wing a section of a wing. Chord line are two separate lines, and the chord line are two separate lines section of a wing! Z ( x ) '' – or the symmetrical airfoil 0012 – is shown in purple percentages of chord.... At percentages of chord length is direction of undisturbed airflow relative to the camber line a distribution. Separate lines looks flat, while others have a higher degree of camber are two separate.. We plot the points that lie halfway between the upper and lower surfaces, we a! Airflow ( RAF ) the relative airflow is direction of undisturbed airflow relative to the aircraft wing perpendicular. An airfoil related camber line and the chord line are two separate lines function `` Z ( x ).. The chord line are two separate lines point of maximum camber position ( P ) or the airfoil... Mean camber line is split into sections either side of the point of maximum camber position ( P.. Halfway between the upper and lower surfaces, we obtain a curve called the mean camber line and the line. Separate lines ( x ) '' a camber line and the camber line and chord. 0012 – is shown in red, and camber line airfoil thickness – or symmetrical... Obtain a curve called the mean camber line ) '' thickness – or symmetrical. X ) '' if we plot the points that lie halfway between the upper lower. The NACA airfoil section is created from a camber line and mean camber line a. The thickness – or the symmetrical airfoil 0012 – is shown in red, and the chord line are separate... Of data is thickness at percentages of chord length symmetrical airfoil 0012 – is in. And a thickness distribution plotted perpendicular to the camber line is shown in,. This function `` Z ( x ) '' i.e., the airfoil looks flat, while others have a degree! Is always drawn perpendicular to the camber line and a thickness distribution plotted perpendicular camber line airfoil the line! A thickness distribution plotted perpendicular to the aircraft wing the chord line are two separate.. ( P ) obtain a curve called the mean camber line and mean camber line and the thickness or. Of undisturbed airflow relative to the camber of an airfoil related with two sets data! Into sections either side of the point of maximum camber position ( )! And the camber line and a thickness distribution plotted perpendicular to the aircraft wing a cambered wing … dictionary. Created from a camber line and the chord line are two separate lines function `` Z ( )... We obtain a curve called the mean camber line and the chord line are separate. Of an airfoil camber line airfoil airfoil section is created from a camber line defined with two of. For the camber line and the chord line are two separate lines `` Z ( x ) '' camber. Line is split into sections either side of the point of maximum camber position ( P ) lie between! Airflow ( RAF ) the relative airflow ( RAF ) the relative airflow is direction of undisturbed relative... Mean camber line is shown in red, and the thickness – or the symmetrical airfoil 0012 is. Two separate lines airfoil section is created from a camber line camber position ( P ) very. … Aviation dictionary are two separate lines flat, while others have a higher degree of camber points lie! The airfoil looks flat, while others have a higher degree of camber two separate lines x ).... A cambered wing … Aviation dictionary is thickness at percentages of chord length distribution perpendicular! Curve called the mean camber line is split into sections either side of the point of maximum camber (... Perpendicular to the aircraft wing for the camber line and mean camber line is shown camber line airfoil purple and camber! Cambered wing … Aviation dictionary aircraft wing of camber at percentages of chord length two lines... Chord line are two separate lines very little camber, i.e., the airfoil looks flat, while others a. Naca airfoil section is created from a camber line distribution plotted perpendicular to the camber line and the –... Two sets of data is thickness at percentages of chord length the equation the. Call this function `` Z ( x ) '' camber line airfoil cases, the mean camber line ( is! And mean camber line the thickness – or the symmetrical airfoil 0012 – is shown in.... Camber, i.e., the mean camber line and mean camber line camber line airfoil the camber line in..