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Nose cone design
Geometry and construction of the foremost tip of airplanes, spacecraft and projectiles From Wikipedia, the free encyclopedia
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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.
This article includes a list of general references, but it lacks sufficient corresponding inline citations. (July 2018) |

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Nose cone shapes and equations
Summarize
Perspective
Conic
Conic nose cone render and profile with parameters shown.
Spherically blunted conic
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
Bi-conic nose cone render and profile with parameters shown.
Tangent ogive
Tangent ogive nose cone render and profile with parameters and ogive circle shown.
Spherically blunted tangent ogive
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
Secant ogive nose cone render and profile with parameters and ogive circle shown.
Alternate secant ogive render and profile which show a bulge due to a smaller radius.
Elliptical
Elliptical nose cone render and profile with parameters shown.
Parabolic
Half (K′ = 1/2)
Three-quarter (K′ = 3/4)
Full (K′ = 1)
Renders of common parabolic nose cone shapes.
Power series
Half (n = 1/2) Three-quarter (n = 3/4) |
Haack series
LD-Haack (Von Kármán) (C = 0) 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

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

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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