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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By using this site, you agree to the Terms of Use and Privacy Policy. 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 damaged aircraft.

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. Incidence angles can also be added to the wing and horizontal manusl.

United States Air Force Stability and Control Digital DATCOM – Wikipedia

By default, only the data for the aircraft is output, but additional configurations can be output:. This problem can be overcome datcon using experimental data for the wing-body using non-straight tapered wing.

There is no method to input twin vertical tails mounted on the fuselage, although there is a method for H-Tails. The basic output includes:. The canard must be specified as the forward lifting surface i. 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 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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March Learn how and when to remove this template message. There mwnual been some research manusl using Digital DATCOM in conjunction with wind tunnel studies to predict aerodynamics mahual structurally impaired aircraft. For each configuration, stability coefficients and derivatives are output at each angle of attack specified.

Three damage-configurations are studied at supersonic speeds. Dynamic derivatives are not output for aircraft that have wings that are not straight-tapered or have leading edge extensions.

For complete aircraft configurations, downwash data is also included.

Printed Manuals for USAF Datcom

However, manuzl its day, the program was an advanced estimation tool, and certainly much faster than plowing through pages and pages of engineering texts. Please help to improve this article by introducing more precise citations. The methodology can be used to quickly generate aerodynamic model for damaged aircraft for simulation and reconfigurable control. Views Read Edit View history. Up to 9 flap deflections can be analyzed at each Mach-altitude combination.

According to the manual, there is no any input parameters which define the geometriy of rudder. This page was last edited on 22 Decemberat The simplification affects the coefficient of drag for the aircraft.

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

Vatcom from ” https: 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. There have also been hooks placed in the DIGDAT that allow for 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.

The X- and Z- coordinates are needed for the winghorizontal tailand vertical tail in order for the aircraft to be synthesized correctly. The basic parameters such as root chord, tip chord, half-span, twistdihedral and sweep are input. The new input file mxnual allows the user to place comments in the input file.

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Articles lacking in-text citations from March All articles lacking in-text citations. This problem can be addressed by superposition of lifting surfaces through the experimental input option. All dimensions are taken in feet and degrees unless specified otherwise. There are intentions among those that use this package to improve the overall package, through an easier user interface, as well as more comprehensive output data.

United States Air Force Stability and Control Digital DATCOM

This article includes a list of referencesbut its sources remain unclear because it has insufficient inline citations. 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.

Manal 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.

An alpha version of the program was released November 1, to the general public. A maximum of Mach-altitude combinations can be run at once, with up to 20 angles of attack for each combination. For supersonic analysis, additional parameters can be input. Data tables can easily be output to the screen or to PNG files for inclusion into reports.

The theoretical wing area, mean aerodynamic amnualand wing span are input along with a parameter defining the surface roughness of the aircraft.