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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By default, only the data for the aircraft is output, but additional configurations can be output:. The methodology can be used to quickly generate aerodynamic model for damaged aircraft for simulation and reconfigurable control.

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 mahual.

The basic parameters such as root chord, tip chord, half-span, twistdihedral and sweep are input.

The values obtained can be used to calculate meaningful aspects of flight dynamics. Up to 20 stations can be specified with the fuselage half-width, upper coordinate and lower coordinate being defined at each station. Raw results from the code datco good correlation with wind tunnel data at very low angles of attack, but accuracy deteriorates rapidly as the angle of attack increases.

United States Air Force Stability and Control Digital DATCOM

This problem can be addressed by approximating the twin vertical tails as a single equivalent vertical tail mounted to the fuselage. There is no method to input twin vertical tails mounted on the fuselage, although there is a method manuap H-Tails.

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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. The report consists of. Articles lacking in-text citations from March All articles lacking in-text citations. All dimensions are taken in feet and degrees unless specified otherwise.

USAF Digital Datcom

The basic output includes:. Views Read Edit View history. From Wikipedia, the free encyclopedia. The X- and Z- coordinates are needed for the winghorizontal tailand vertical tail in order for the aircraft to be synthesized correctly.

Dynamic derivatives are not output for aircraft that have wings that msnual not straight-tapered or have leading edge extensions. However, in its day, the program was an advanced estimation tool, and certainly much faster than plowing through pages and pages of engineering texts. Three damage-configurations are studied at supersonic speeds.

There has been some research in using Digital DATCOM in conjunction with wind tunnel studies to predict aerodynamics of structurally impaired aircraft. This problem can be addressed by superposition of lifting surfaces through the experimental input option. Retrieved from ” https: Data tables can easily be output to the screen or to PNG files for inclusion into reports. According to the manual, there is no any input parameters which define the geometriy of rudder.

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An alpha version of the program was released November 1, to the general public. This page was last edited on 22 Decemberat 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 The theoretical wing area, mean aerodynamic chordand wing span are input along with a parameter defining the surface roughness of the aircraft.

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.

The simplification affects the coefficient of drag for the aircraft. This problem can be overcome by using experimental data for the wing-body using non-straight tapered wing. OpenDatcom incorporates all the basic non-experimental functionality supported by the Digital DATCOM while providing real-time input error and bounds checking.

Printed Manuals for USAF Datcom

March Learn how and when to remove this template message. 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. For supersonic analysis, additional parameters can be input.