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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A new methodology is then proposed which combines the experimental results of healthy aircraft with the predicted aerodynamics of the damaged cases, to yield better correlation between experimental and predicted aerodynamic coefficients for manaul aircraft.

There have also been hooks placed in the DIGDAT that allow mannual alternate outputs in addition to the original output format, which is columns wide and slightly user abusive if you intend to import the data into another application.

United States Air Force Stability and Control Digital DATCOM

Data tables can easily be output to the screen or to PNG files for inclusion into reports. Incidence angles can also be added to the wing and horizontal tail. The basic output includes:. By default, only the data for the aircraft is output, but additional configurations can be output:. This problem can be overcome by using experimental data for the wing-body using non-straight tapered wing. March Learn how and when to remove this template message. There is no method to input twin vertical tails mounted on the fuselage, although there is a method for H-Tails.

USAF Digital Datcom

The simplification affects the coefficient of drag for the aircraft. According to the manual, there is no any input parameters which define the geometriy of rudder. There are intentions among those that use this package to improve the overall package, through an easier catcom interface, as well as more comprehensive output data.

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An alpha version of the program was mnual November 1, to the general public. The methodology can be used to quickly generate aerodynamic model for damaged aircraft for simulation and reconfigurable control. Views Read Edit View history. Additionally, custom airfoils can be input using the appropriate namelists. For each configuration, stability coefficients and derivatives are output at each angle of attack specified.

The new input file format allows the user to place comments in the input file. All dimensions are taken datom feet and degrees unless specified otherwise. This problem maunal be addressed by superposition of lifting surfaces through the experimental input option. The theoretical wing area, mean aerodynamic chordand wing span are input along with a parameter defining the surface roughness of the aircraft.

adtcom 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.

From Wikipedia, the free encyclopedia.

Printed Manuals for the USAF Datcom

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. 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 dacom that point.

While the original DIGDAT program has been ratcom 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 There has been some research in using Digital DATCOM in conjunction with wind tunnel studies to predict aerodynamics of structurally impaired aircraft.

Up to 20 stations dahcom be specified with the fuselage half-width, upper coordinate and lower coordinate being defined at each station. The values obtained can be used to calculate meaningful aspects of flight dynamics. Please help to improve this article by introducing more precise citations.

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Raw results from the code provide good correlation with wind tunnel data at very datcok angles of attack, but accuracy deteriorates rapidly as the angle of attack increases. This article includes a list of referencesbut its sources remain unclear because it has insufficient inline citations.

Articles lacking in-text citations from March All articles lacking in-text citations. Dynamic derivatives are not output for aircraft that have wings that are not straight-tapered or have leading edge extensions. Digital DATCOM requires an input file containing a geometric description of an aircraft, and outputs its corresponding dimensionless stability derivatives according datdom the specified flight conditions.

The X- and Z- coordinates are needed for the winghorizontal tailand vertical tail in order for the aircraft to be synthesized correctly. A maximum of Mach-altitude combinations can be run at once, with up to datfom angles of attack for each combination. The basic parameters such as root chord, tip chord, half-span, twistdihedral and sweep are input.

OpenDatcom incorporates all the basic non-experimental functionality supported by the Digital DATCOM while providing real-time input error and bounds checking.

Up to 9 flap deflections can be analyzed at each Maunal combination. This page was last edited on 22 Decemberat The report consists of. By using this msnual, you agree to the Terms of Use and Privacy Policy. For supersonic analysis, additional parameters can be input.