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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.

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.

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^{[further explanation needed]} for its drag characteristics. The sides of a conical profile are straight lines, so the diameter equation is simply

Cones are sometimes defined by their half angle, :

- and

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:

- where:
- is the radius of the spherical nose cap.

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

And the apex point can be found from:

A bi-conic nose cone shape is simply a cone with length L_{1} stacked on top of a frustum of a cone (commonly known as a *conical transition section* shape) with length L_{2}, where the base of the upper cone is equal in radius R_{1} to the top radius of the smaller frustum with base radius R_{2}.

- L = L
_{1}+ L_{2}

- for :

*half angle* :

- and

- for :

*half angle* :

- and

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.

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

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

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

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:

- where:
- is the radius and is the center of the spherical nose cap.

And the apex point can be found from:

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 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.

- and

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

If the chosen is less than the tangent ogive , 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 half the length of the nose cone.

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.^{[further explanation needed]} This is not a shape normally found in professional rocketry.^{[why?]} If *R* equals *L*, this is a hemisphere.

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 power series below. (The parabolic shape is also often confused with the elliptical shape.)

For :

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.

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 (described above). 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 joint between nose cone and body 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 the *y = R(x/L)^n* curve about the x-axis for values of *n* less than 1. The factor *n* controls the bluntness of the shape. For values of *n* above about 0.7, the tip is fairly sharp. As *n* decreases towards zero, the power series nose shape becomes increasingly blunt.

- For

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

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; see also Sears–Haack body. 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^{[citation needed]} except for the case where *C = 2/3*. However, the discontinuity is usually so slight as to be imperceptible. For *C > 2/3*, Haack nose cones bulge to a maximum diameter greater than the base diameter. Haack nose tips do not come to a sharp point, but are slightly rounded.

Where:

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

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*.

Main article: Drag-resistant aerospike

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.

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.^{[attribution needed]} This chart generally agrees with more detailed, but less comprehensive data found in other references (most notably the USAF Datcom).

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.

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.

- "The Descriptive Geometry Of Nose Cones".
*The Descriptive Geometry Of Nose Cones - by Gary A. Crowell Sr*. Retrieved 2011. - "Nose cones equations".
*Nose Cones excel sheet by Kemal Payza*. Retrieved October 23, 2009. - Department of Defense Military Design Handbook (1990).
*Design of Aerodynamically Stabilized Free Rockets*. U.S. Army Missile Command. MIL-HDBK-762(MI).[1] - Geschoßformen kleinsten Wellenwiderstandes by W. Haack, Bericht 139 der Lilienthal-Gesellschaft (1941)
^{[dead link]} - Chin SS. (1961).
*Missile Configuration Design*. McGraw-Hill Book Co., Inc., New York.