Nose cone design

Nose cone design

Given the problem of the aerodynamic design of the nose cone section of any vehicle or body meant to travel through a compressible fluid medium (such as a rocket or aircraft, missile or bullet), an important problem is the determination of the nose cone geometrical shape for optimum performance. For many applications, such a task requires the definition of a solid of revolution shape that experiences minimal resistance to rapid motion through 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.

Nose cone general dimensions.svg


Nose cone conical.svg

A very common nose cone shape is a simple cone. This shape is often chosen for its ease of manufacture, and is also often (mis)chosen for its drag characteristics. The sides of a conical profile are straight lines, so the diameter equation is simply

y = {xR \over L}

Cones are sometimes defined by their half angle, \phi \; :

\phi = \arctan \left({R \over L}\right) and y = x \tan(\phi)\;

Spherically Blunted Cone

Spherically blunted cone geometry.svg

In practical applications, a conical nose is often blunted by capping it with a segment of a sphere. The tangency point where the sphere meets the cone can be found from:

x_t = \frac{L^2}{R} \sqrt{ \frac{r_n^2}{R^2 + L^2} }
y_t = \frac{x_t R}{L}
rn is the radius of the spherical nose cap.

The center of the spherical nose cap can be found from:

x_o = x_t + \sqrt{ r_n^2 - y_t^2}

And the apex point can be found from:

xa = xorn


A bi-conic nose cone shape is simply a cone with length L1 stacked on top of a frustum of a cone (commonly known as a conical transition section shape) with length L2, where the base of the upper cone is equal in radius R1 to the top radius of the smaller frustum with base radius R2.

Nose cone bi-conic.png
L = L1 + L2
  • for 0 \le x \le L_1  : y = {xR_1 \over L_1}

half angle :

\phi_1 = \arctan \left({R_1 \over L_1}\right) and y = x \tan(\phi_1)\;
  • for L_1 \le x \le L : y = R_1 + {(x - L_1)(R_2-R_1)\over L_2}

half angle :

\phi_2 = \arctan \left({R_2 - R_1 \over L_2}\right) and y = R_1 + (x - L_1) \tan(\phi_2)\;

Tangent ogive

Next to a simple cone, the tangent ogive shape is the most familiar in 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.

Nose cone tangent ogive.png

The radius of the circle that forms the ogive is called the Ogive Radius ρ and it is related to the length and base radius of the nose cone as expressed by the formula:

\rho = {R^2 + L^2\over 2R}

The radius y at any point x, as x varies from 0 to L is:

y = \sqrt{\rho^2 - (L - x)^2}+R - \rho

The nose cone length, L, must be equal to, or less than the Ogive Radius ρ. If they are equal, then the shape is a hemisphere.

Spherically blunted tangent ogive

Spherically blunted tangent ogive geometry.svg

A tangent ogive nose is often blunted by capping it with a segment of a sphere. The tangency point where the sphere meets the tangent ogive can be found from:

x_o = L - \sqrt{ (\rho - r_n)^2 - (\rho - R)^2}
y_t = \frac{ r_n(\rho - R)}{\rho - r_n}
x_t = x_o - \sqrt{r_n^2 - y_t^2}
rn is the radius and xo is the center of the spherical nose cap.

And the apex point can be found from:

xa = xorn

Secant ogive

Nose cone secant ogive 1.png

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 ρ 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.

\rho > {R^2 + L^2 \over 2R} and \alpha = \arctan \left({R \over L}\right) - \arccos \left({\sqrt{L^2+R^2} \over 2\rho}\right)

Then the radius y at any point x as x varies from 0 to L is:

y = \sqrt{\rho^2-(\rho\cos\alpha-x)^2}+\rho\sin\alpha
Nose cone secant ogive 2.png

If the chosen ρ is less than the tangent ogive ρ, 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.

{2L} < \rho < {R^2+L^2 \over 2R}


Nose cone elliptical.svg

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 hemisphere.

y = R \sqrt{1 - {x^2 \over L^2}}


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 0 \le K' \le 1 : y = R\left({2 ({x \over L}) - K'({x \over L})^2 \over 2 - K'}\right)

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 and a 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 0 \le n \le 1 : y = R\left({x \over L}\right)^n


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 Haack Series shapes are not constructed from geometric figures. The shapes are instead mathematically derived for the purpose of minimizing 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.

\theta = \arccos \left(1 - {2x \over L}\right)
y = {R\sqrt{\theta - {\sin(2\theta)\over 2} + C \sin^3 \theta} \over \sqrt{\pi}}


C = 1/3 for LV-Haack
C = 0 for LD-Haack

Von Kármán

The Haack series giving minimum drag for the given length and diameter, LD-Haack, is commonly referred to as the Von Kármán or the Von Kármán Ogive.


See Drag-resistant aerospike

Nose cone drag characteristics

For aircraft and rockets, below 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 USAF Datcom).

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 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. 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 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.


Wikimedia Foundation. 2010.

Игры ⚽ Нужна курсовая?

Look at other dictionaries:

  • Nose cone — For the Transformers character, see Nosecone (Transformers). A nose cone that contained one of the Voyager spacecraft, mounted on top of a Titan III/Centaur launch vehicle …   Wikipedia

  • Inlet cone — Infobox Aviation name=Inlet cone caption=Inlet cone of a MiG 21MFInlet cones (sometimes called shock cones) are a component of some supersonic aircraft. They are primarily used on ramjets, such as the turboramjets of the SR 71 or the pure ramjets …   Wikipedia

  • Nuclear weapon design — The first nuclear weapons, though large, cumbersome and inefficient, provided the basic design building blocks of all future weapons. Here the Gadget device is prepared for the first nuclear test: Trinity. Nuclear weapon designs are physical,… …   Wikipedia

  • Teller–Ulam design — The basics of the Teller–Ulam design. Radiation from a primary fission bomb compresses a secondary section containing both fission and fusion fuel. The compressed secondary is heated from within by a second fission explosion. The Teller–Ulam… …   Wikipedia

  • Aérodynamique de la pointe avant — La conception aérodynamique de la pointe avant de tout véhicule ou d un objet se déplaçant un milieu fluide compressible (comme une fusée ou un avion, un missile ou une balle), est un problème important. Il consiste a déterminer la forme de la… …   Wikipédia en Français

  • Dragon (spacecraft) — SpaceX Dragon spacecraft Artist s rendering of the cargo variant of the SpaceX Dragon spacecraft (bottom) berthing to the International Space Station (top). Description Role: Commercial: various roles that put humans and cargo into LEO …   Wikipedia

  • Very-low-drag bullet — Very low drag bullets (VLD) are primarily a small arms ballistics development of the 1980s–1990s, driven by shooters desire for bullets that will give a higher degree of accuracy and kinetic efficiency, especially at extended ranges. To achieve… …   Wikipedia

  • Wolfgang Haack — Wolfgang Siegfried Haack (born April 24, 1902 in Gotha; November 28, 1994 in Berlin) was a German mathematician.LifeWolfgang Haack studied mechanical engineering in Hanover and Mathematics in Jena. There, he earned his doctorate in 1926 at the… …   Wikipedia

  • Aerodynamics — is a branch of dynamics concerned with studying the motion of air, particularly when it interacts with a moving object. Aerodynamics is closely related to fluid dynamics and gas dynamics, with much theory shared between them. Aerodynamics is… …   Wikipedia

  • Commercial Crew Development — Commercial Crew Program logo Commercial Crew and Cargo …   Wikipedia

Share the article and excerpts

Direct link
Do a right-click on the link above
and select “Copy Link”