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Nose cone design

Geometry and construction of the foremost tip of airplanes, spacecraft and projectiles From Wikipedia, the free encyclopedia

Nose cone design
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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, shell 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.

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General parameters used for constructing nose cone profiles.
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Nose cone shapes and equations

Summarize
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Conic

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Conic nose cone render and profile with parameters shown.

Spherically blunted conic

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Spherically blunted conic nose cone render and profile with parameters shown.

In practical applications such as re-entry vehicles, 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, using similar triangles, from:

where rn is the radius of the spherical nose cap.

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

And the apex point, xa can be found from:

Bi-conic

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Bi-conic nose cone render and profile with parameters shown.

Tangent ogive

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Tangent ogive nose cone render and profile with parameters and ogive circle shown.

Spherically blunted tangent ogive

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Spherically blunted tangent ogive nose cone render and profile with parameters shown.

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 rn is the radius and xo is the center of the spherical nose cap.


Secant ogive

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Secant ogive nose cone render and profile with parameters and ogive circle shown.
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Alternate secant ogive render and profile which show a bulge due to a smaller radius.

Elliptical

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Elliptical nose cone render and profile with parameters shown.

Parabolic

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Half (K′ = 1/2)
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Three-quarter (K′ = 3/4)
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Full (K′ = 1)
Renders of common parabolic nose cone shapes.

Power series

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Graphs illustrating power series nose cone shapes
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Half (n = 1/2)
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Three-quarter (n = 3/4)

Haack series

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Graphs illustrating Haack series nose cone shapes
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LD-Haack (Von Kármán) (C = 0)
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LV-Haack (C = 1/3)

Power Series

A power series nosecone is defined by where . will generate a concave geometry, while will generate a convex (or "flared") shape[1]

Parabolic Series

A parabolic series nosecone is defined by where and is series variable. [1]

Haack Series

A Haack series nosecone is defined by where [1]. Parametric formulation can be obtained by solving the formula for .

Von Kármán Ogive

The LD-Haack ogive is a special case of the Haack series with minimal drag for a given length and diameter, and is defined as a Haack series with C = 0, commonly called the Von Kármán or Von Kármán ogive. A cone with minimal drag for a given length and volume can be called a LV-Haack series, defined with .[1]

Aerospike

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An aerospike on the UGM-96 Trident I

An aerospike can be used to reduce the forebody pressure acting on supersonic aircraft. The aerospike creates a detached shock ahead of the body, thus reducing the drag acting on the aircraft.

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Nose cone drag characteristics

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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).

See also

Further reading

  • Haack, Wolfgang (1941). "Geschoßformen kleinsten Wellenwiderstandes" (PDF). Bericht 139 der Lilienthal-Gesellschaft für Luftfahrtforschung: 14–28. Archived from the original (PDF) on 2007-09-27.
  • U.S. Army Missile Command (17 July 1990). Design of Aerodynamically Stabilized Free Rockets. U.S. Government Printing Office. MIL-HDBK-762(MI).

References

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