Search results
Results From The WOW.Com Content Network
General parameters used for constructing nose cone profiles. 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.
English: Render from SolidWorks CAD program of a spherically blunted conic-shaped rocket nose cone with a length of 18 inches, a primary radius of 4 inches, and a nose cap radius of 1 inch. Date 17 July 2018
A nose cone is the conically shaped forwardmost section of a rocket, guided missile or aircraft, designed to modulate oncoming airflow behaviors and minimize aerodynamic drag. Nose cones are also designed for submerged watercraft such as submarines , submersibles and torpedoes , and in high-speed land vehicles such as rocket cars and velomobiles .
A drag-reducing aerospike is a device (see nose cone design) used to reduce the forebody pressure aerodynamic drag of blunt bodies at supersonic speeds. The aerospike creates a detached shock ahead of the body. Between the shock and the forebody a zone of recirculating flow occurs which acts like a more streamlined forebody profile, reducing ...
For premium support please call: 800-290-4726 more ways to reach us
English: Render from SolidWorks CAD program of a bi-conic-shaped rocket nose cone with a total length of 18 inches, a primary radius of 4 inches, a secondary (tip) section length of 6 inches, and a secondary radius of 2 inches.
English: A series of plots given by the formula and the values specified under Nose Cone Design#Power Series.Note that this diagramme has arbitrary width and height and will not necessarily show Length and Radius at a practical ratio.
Artist's rendering of a payload fairing being jettisoned An example of clamshell fairing of Falcon 9 during testing, 27 May 2013. A payload fairing is a nose cone used to protect a spacecraft payload against the impact of dynamic pressure and aerodynamic heating during launch through an atmosphere.