Nose cone design
1693865
193805514
2008-02-24T23:33:09Z
Gaius Cornelius
293907
Tidy using [[Project:AutoWikiBrowser|AWB]]
Given the problem of the [[aerodynamic]] [[design]] of the [[nose cone]] section of any vehicle meant to travel through a compressible fluid medium (such as a [[rocket]] or [[aircraft]]), the main problem at hand is the determination of the [[nose cone]] geometrical shape. For many applications, such a task requires the definition of [[solid of revolution]] shape that experiences minimal resistance to rapid motion through a such a fluid medium, which consists of elastic particles.
== Nose cone shapes and equations ==
===General dimensions===
In all of the following nose cone shape equations, ''L'' is the overall length of the nose cone and ''R'' is the radius of the base of the nose cone. ''y'' is the radius at any point ''x'', as ''x'' varies from 0, at the tip of the nose cone, to ''L''. The equations define the 2-dimensional profile of the nose shape. The full [[body of revolution]] of the nose cone is formed by rotating the profile around the centerline ''(C/L)''. Note that the equations describe the 'perfect' shape; practical nose cones are often blunted or truncated for manufacturing or aerodynamic reasons.
[[Image:Nose cone general.png]]
===Conical===
[[Image:nose cone conical.png|right]]
A very common nose cone shape is a simple [[cone (geometry)|cone]]. This shape is often chosen for its ease of manufacture, and is also often (mis)chosen for its [[Drag (physics)|drag]] characteristics. The sides of a conical profile are straight lines, so the diameter equation is simply
:<math>y = {xR \over L}</math>
Cones are sometimes defined by their half angle, <math>\phi \;</math> :
:<math>\phi = \arctan \left({R \over L}\right)</math> and <math>y = x \tan(\phi)\;</math>
===Bi-conic===
A bi-conic nose cone shape is simply a cone with length L<sub>1</sub> stacked on top of a [[frustum]] of a cone (commonly known as a ''conical transition section'' shape) with lengh L<sub>2</sub>, where the base of the upper cone is equal in radius R<sub>1</sub> to the top radius of the smaller frustum with base radius R<sub>2</sub>.
[[Image:nose cone bi-conic.png|right]]
:L = L<sub>1</sub> + L<sub>2</sub>
* for <math>0 \le x \le L_1 </math> : <math>y = {xR_1 \over L_1}</math>
''half angle'' :
:<math>\phi_1 = \arctan \left({R_1 \over L_1}\right)</math> and <math>y = x \tan(\phi_1)\;</math>
* for <math>L_1 \le x \le L</math> : <math>y = R_1 + {(x - L_1)(R_2-R_1)\over L_2}</math>
''half angle'' :
:<math>\phi_2 = \arctan \left({R_2 - R_1 \over L_2}\right)</math> and <math>y = R_1 + (x - L_1) \tan(\phi_2)\;</math>
===Tangent ogive===
Next to a simple cone, the tangent [[ogive]] shape is the most familiar in [[model rocketry|hobby rocketry]]. The profile of this shape is formed by a segment of a [[circle]] such that the rocket body is [[tangent]] to the curve of the nose cone at its base; and the base is on the radius of the circle. The popularity of this shape is largely due to the ease of constructing its profile.
[[Image:nose cone tangent ogive.png]]
The radius of the circle that forms the ogive is called the Ogive Radius <math>\rho</math> and it is related to the length and base radius of the nose cone as expressed by the formula:
:<math>\rho = {R^2 + L^2\over 2R}</math>
The radius ''y'' at any point ''x'', as ''x'' varies from ''0'' to ''L'' is:
:<math>y = \sqrt{\rho^2 - (x - L)^2}+R - \rho</math>
The nose cone length, ''L'', must be equal to, or less than the Ogive Radius <math>\rho</math>. If they are equal, then the shape is a [[Sphere|hemisphere]].
===Secant ogive===
[[Image:nose cone secant ogive 1.png|right]]
The profile of this shape is also formed by a segment of a circle, but the base of the shape is not on the radius of the circle defined by the ogive radius. The rocket body will '''not''' be tangent to the curve of the nose at its base. The Ogive Radius <math>\rho</math> is not determined by ''R'' and ''L'' (as it is for a tangent ogive), but rather is one of the factors to be chosen to define the nose shape. If the chosen Ogive Radius of a Secant Ogive is greater than the Ogive Radius of a Tangent Ogive with the same ''R'' and ''L'', then the resulting Secant Ogive appears as a Tangent Ogive with a portion of the base truncated.
:<math>\rho > {R^2 + L^2 \over 2R}</math> and <math>\alpha = \arctan \left({R \over L}\right) - \arccos \left({\sqrt{L^2+R^2} \over 2\rho}\right)</math>
Then the radius ''y'' at any point ''x'' as ''x'' varies from ''0'' to ''L'' is:
:<math>y = \sqrt{\rho^2-(x-\rho\cos\alpha)^2}+\rho\sin\alpha</math>
[[Image:nose cone secant ogive 2.png|right]]
If the chosen <math>\rho</math> is less than the tangent ogive <math>\rho</math>, then the result will be a Secant Ogive that bulges out to a maximum diameter that is greater than the base diameter. The classic example of this shape is the nose cone of the [[Honest John]]. Also, the chosen ogive radius must be greater than twice the length of the nose cone.
:<math>{L \over 2} < \rho < {R^2+L^2 \over 2R}</math>
===Elliptical===
[[Image:nose cone elliptical.png|right]]
The profile of this shape is one-half of an [[ellipse]], with the major axis being the centerline and the minor axis being the base of the nose cone. A rotation of a full ellipse about its major axis is called a [[prolate]] spheroid, so an elliptical nose shape would properly be known as a prolate hemispheroid. This shape is popular in subsonic flight (such as [[model rocketry]]) due to the blunt nose and tangent base. This is not a shape normally found in professional rocketry. If ''R'' equals ''L'', this is a [[Sphere|hemisphere]].
:<math>y = R \sqrt{1 - {x^2 \over L^2}}</math>
===Parabolic===
This nose shape is not the blunt shape that is envisioned when people commonly refer to a ‘parabolic’ nose cone. The Parabolic Series nose shape is generated by rotating a segment of a [[parabola]] around a line parallel to its [[Latus rectum]]. This construction is similar to that of the Tangent Ogive, except that a parabola is the defining shape rather than a circle. Just as it does on an Ogive, this construction produces a nose shape with a sharp tip. For the blunt shape typically associated with a parabolic nose, see the Power Series. (The parabolic shape is also often confused with the elliptical shape.)
For <math>0 \le K' \le 1</math> : <math>y = R\left({2 ({x \over L}) - K'({x \over L})^2 \over 2 - K'}\right) </math>
K’ can vary anywhere between 0 and 1, but the most common values used for nose cone shapes are:
:K’ = 0 for a cone
:K’ = 0.5 for a 1/2 parabola
:K’ = 0.75 for a 3/4 parabola
:K’ = 1 for a full parabola
For the case of the full Parabola (K’=1) the shape is [[tangent]] to the body at its base, and the base is on the axis of the parabola. Values of K’ less than one result in a ‘slimmer’ shape, whose appearance is similar to that of the secant ogive. The shape is no longer tangent at the base, and the base is parallel to, but offset from, the axis of the parabola.
===Power series===
The Power Series includes the shape commonly referred to as a ‘parabolic’ nose cone, but the shape correctly known as a parabolic nose cone is a member of the Parabolic Series, and is something completely different. The Power Series shape is characterized by its (usually) blunt tip, and by the fact that its base is not tangent to the body tube. There is always a discontinuity at the nose cone / body joint that looks distinctly non-aerodynamic. The shape can be modified at the base to smooth out this discontinuity. Both a flat-faced [[cylinder (geometry)|cylinder]] and a [[cone (geometry)|cone]] are shapes that are members of the Power Series.
The Power series nose shape is generated by rotating a [[parabola]] about its axis. The base of the nose cone is parallel to the [[latus rectum]] of the parabola, and the factor ''n'' controls the ‘bluntness’ of the shape. As ''n'' decreases towards zero, the Power Series nose shape becomes increasingly blunt. At values of ''n'' above about 0.7, the tip becomes sharp.
For <math>0 \le n \le 1</math> : <math>y = R\left({x \over L}\right)^n</math>
Where:
:n = 1 for a cone
:n = 0.75 for a 3/4 power
:n = 0.5 for a 1/2 power (parabola)
:n = 0 for a cylinder
===Haack series===
Unlike all of the nose cone shapes above, the [[Wolfgang Haack|Haack]] Series shapes are not constructed from geometric figures. The shapes are instead mathematically derived for the purpose of minimizing [[Drag (physics)|drag]]. While the series is a continuous set of shapes determined by the value of ''C'' in the equations below, two values of ''C'' have particular significance: when ''C = 0'', the notation ‘LD’ signifies minimum drag for the given length and diameter, and when ''C = 1/3'', ‘LV’ indicates minimum drag for a given length and volume. The Haack series nose cones are not perfectly tangent to the body at their base, however the discontinuity is usually so slight as to be imperceptible. Haack nose tips do not come to a sharp point, but are slightly rounded.
:<math>\theta = \arccos \left(1 - {2x \over L}\right)</math>
:<math>y = {R\sqrt{\theta - {\sin(2\theta)\over 2} + C \sin^3 \theta} \over \sqrt{\pi}}</math>
Where:
:C = 1/3 for LV-Haack
:C = 0 for LD-Haack (also known as the [[Theodore von Kármán|Von Kármán]] or the ''Von Kármán [[Ogive]]'')
==Nose cone drag characteristics==
For aircraft and rockets, below [[Mach number|Mach]] .8, the nose pressure drag is essentially zero for all shapes. The major significant factor is friction drag, which is largely dependent upon the [[wetted area]], the surface smoothness of that area, and the presence of any discontinuities in the shape. For example, in strictly subsonic rockets a short, blunt, smooth elliptical shape is usually best. In the [[transonic]] region and beyond, where the pressure drag increases dramatically, the effect of nose shape on drag becomes highly significant. The factors influencing the pressure drag are the general shape of the nose cone, its fineness ratio, and its bluffness ratio.
===Influence of the general shape===
Many references on nose cone design contain empirical data comparing the drag characteristics of various nose shapes in different flight regimes. The chart shown here seems to be the most comprehensive and useful compilation of data for the flight regime of greatest interest. This chart generally agrees with more detailed, but less comprehensive data found in other references (most notably the [[Missile Datcom|USAF Datcom]]).
[[Image:Nose cone drag comparison.png|none|frame|Comparison of drag characteristics of various nose cone shapes in the [[transonic]] to low-mach regions. Rankings are: superior (1), good (2), fair (3), inferior (4).]]
In many nose cone designs, the greatest concern is flight performance in the transonic region from 0.8 to 1.2 Mach. Although data is not available for many shapes in the transonic region, the table clearly suggests that either the Von Kármán shape, or Power Series shape with n = 1/2, would be preferable to the popular Conical or Ogive shapes, for this purpose.
This observation goes against the often-repeated conventional wisdom that a conical nose is optimum for "Mach-breaking". Fighter aircraft are probably good examples of nose shapes optimized for the transonic region, although their nose shapes are often distorted by other considerations of avionics and inlets. For example, an [[F-16 Fighting Falcon| F-16]] nose appears to be a very close match to a Von Karman shape.
===Influence of the Fineness Ratio===
The ratio of the length of a nose cone compared to its base diameter is known as the ‘Fineness Ratio’. This is sometimes also called the ‘Aspect Ratio’, though that term is usually applied to wings and fins. The term ‘fineness ratio’ is often applied to the entire vehicle, considering the overall length and diameter. The length/diameter relation is also often called the ‘Caliber’ of a nose cone.
At supersonic speeds, the fineness ratio has a very significant effect on nose cone wave drag, particularly at low ratios; but there is very little additional gain for ratios increasing beyond 5:1. As the fineness ratio increases, the wetted area, and thus the skin friction component of drag, is also going to increase. Therefore the minimum drag fineness ratio is ultimately going to be a tradeoff between the decreasing wave drag and increasing friction drag.
==References==
* {{cite web | title=The Descriptive Geometry Of Nose Cones | work=The Descriptive Geometry Of Nose Cones - Word document by Gary A. Crowell Sr. | url=http://myweb.cableone.net/cjcrowell/VCPMAIN.htm | accessyear=2006}}
* {{cite web | title=Nose cones equations | work=Nose Cones excel sheet by Kemal Payza | url=http://www.info-central.org/design_nosecones.shtml | accessmonthday=November 25 | accessyear=1999}}
* {{cite book | author=Department of Defense Military Design Handbook | title=Design of Aerodynamically Stabilized Free Rockets | publisher=[[U.S. Army Missile Command]] | year=1990 | id=MIL-HDBK-762(MI)}}[http://rocketsciencebooks.home.att.net/army-aero-design.html]
* [http://www.lima-wiederladetechnik.de/Ballistik/Lilienthal-139-1-Haack.pdf Geschoßformen kleinsten Wellenwiderstandes by W. Haack, Bericht 139 der Lilienthal-Gesellschaft (1941)]
* {{cite book | author=Chin SS. | title=Missile Configuration Design | publisher=McGraw-Hill Book Co., Inc., New York | year=1961 | id=}}
[[Category:Aerodynamics]]
[[Category:Rocketry]]