DATCOM MANUAL PDF

This report is a User’s Manual for the Revision of the Missile Datcom computer program. It supersedes. AFRL-RB-WP-TR How to order printed copies of the USAF Data Compendium for Stability and Control (DATCOM). The user’s manual (on the disc) presents the program capabilities, input This page has links to the user’s manual for Digital Datcom and the.

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The simplification affects the coefficient of drag for the aircraft. The basic parameters such as root chord, tip chord, half-span, twistdihedral and sweep are input.

For each configuration, stability coefficients and derivatives are output at each angle of attack specified. Digital DATCOM requires an input file containing a geometric description of an aircraft, and outputs its corresponding dimensionless stability derivatives according to the specified flight conditions.

An alpha version of the program was released November 1, to the general public. For supersonic analysis, additional parameters can be input.

This problem can be addressed by superposition of lifting surfaces through the experimental input option. However, in its day, the program was an advanced estimation tool, and certainly much faster than plowing through pages and pages of engineering texts. According to the manual, there is no any input parameters which define the geometriy of rudder. Incidence angles can also be added to the wing and horizontal tail.

There has been some research in using Digital DATCOM in conjunction with wind tunnel studies to predict aerodynamics of structurally impaired aircraft.

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From Wikipedia, the free encyclopedia. Three damage-configurations are studied at supersonic speeds. The report consists of. Data tables can manuap be output to the screen or to PNG files for inclusion into reports.

Additionally, custom airfoils can be input using the appropriate namelists. Up to 20 stations can be specified with the fuselage half-width, upper coordinate and lower coordinate being defined at each station. There is no method to input twin vertical tails mounted on the fuselage, although there is a method for H-Tails.

USAF Digital Datcom

Dynamic derivatives are not output datclm aircraft that have wings that are not straight-tapered or have leading edge extensions. March Learn how and when to remove this template message. While the original DIGDAT program has been left relatively untouched, there has been a new front-end created that will allow the user to name the input file with something more significant than FOR OpenDatcom incorporates all the basic non-experimental functionality supported by the Digital DATCOM while providing real-time input error and bounds checking.

There are intentions among those that use this package to improve the overall package, through an easier user interface, as well as more comprehensive amnual data.

This article includes a list of referencesbut its sources remain unclear because it has insufficient inline citations. Up to 9 flap deflections can be analyzed at each Mach-altitude combination.

Digital Datcom

The values obtained can be used to calculate meaningful aspects of flight dynamics. The theoretical wing datfom, mean aerodynamic chordand wing span are input along with a parameter defining the surface roughness of the aircraft. The user can specify whether the Mach number and altitude varies together, the Mach number varies at a constant altitude, or the altitude varies at a constant Mach number.

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A maximum of Mach-altitude combinations can be run at once, with up to 20 angles of attack for each combination. This page was last edited on 22 Decemberat This problem can be addressed by approximating the twin vertical tails as a single equivalent vertical tail mounted to the fuselage. By default, only the data for the aircraft is output, but additional datocm can be output:. The new input file format allows the vatcom to place comments in the input file.

Printed Manuals for the USAF Datcom

The canard must be specified as the forward lifting surface i. DATCOM does not require that the origin for the aircraft has to be the nose of the aircraft; any arbitrary point will do, but all of the dimensions need to be referenced from that point.

Articles lacking in-text citations from March All articles lacking in-text citations. All dimensions are taken in feet and vatcom unless specified otherwise. Raw results from the code provide good correlation with wind tunnel data at very low angles of attack, but accuracy deteriorates rapidly as the angle of attack increases.