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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Articles lacking in-text citations from March All articles lacking in-text citations. Manuao X- and Z- coordinates are needed for the winghorizontal tailand vertical tail in order for the aircraft to be synthesized correctly. There are intentions among those that use this package to improve the overall xatcom, through an easier user interface, as well as more comprehensive output data. Retrieved from ” https: The basic parameters such as root chord, tip chord, half-span, twistdihedral and sweep are input.
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 simplification affects the coefficient of drag for the aircraft. Ddatcom angles can also be added to the manua, and horizontal tail. 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. March Learn how and when to remove this template message. However, in its day, the program was an advanced estimation tool, and certainly much faster than plowing through pages and pages of engineering texts.
Raw results from the darcom provide good correlation with wind tunnel data at very low angles of attack, but accuracy deteriorates rapidly as the angle of attack increases.
According to the manual, there is no any input parameters which define the geometriy of rudder. For supersonic analysis, additional parameters can be input. Three damage-configurations are studied at supersonic speeds. This problem can be addressed by approximating the twin vertical tails as a single equivalent vertical tail mounted to the fuselage. Views Read Edit View history. The report consists of.
The theoretical wing area, mean aerodynamic chordand wing span are input along manial a parameter defining the surface roughness of the aircraft. This problem can be overcome by using experimental data datco the wing-body using non-straight tapered wing. 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.
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.
This article includes a list of referencesbut its sources remain unclear because it has insufficient inline citations. By default, only the data for the aircraft is output, but additional configurations can be output:.
All dimensions are taken in feet and degrees unless specified otherwise. Please help to improve this article by introducing more precise citations. 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 values obtained can be used to calculate meaningful aspects of flight dynamics. Up to 9 flap deflections can be analyzed at each Mach-altitude combination.
There has been some research in using Digital DATCOM in conjunction with wind tunnel studies to predict aerodynamics of structurally impaired aircraft.
United States Air Force Stability and Control Digital DATCOM – Wikipedia
The canard must be specified as the forward lifting surface i. Up to 20 stations can be specified with the fuselage half-width, upper coordinate and lower coordinate being defined at each station.
From Wikipedia, the free encyclopedia. Data tables can easily be output to the screen or to PNG files for inclusion into reports.
The basic output includes:.
An alpha version of the program was released November 1, to the general public. Additionally, custom airfoils can be input using the appropriate namelists. For complete aircraft configurations, downwash data is also included. The methodology can be used to quickly generate aerodynamic model for damaged aircraft for simulation and reconfigurable control. Digital DATCOM requires an input file containing a geometric description of an aircraft, manyal outputs its corresponding dimensionless stability derivatives according to the specified flight conditions.
OpenDatcom incorporates all the basic non-experimental functionality supported by the Digital DATCOM while providing real-time input error and bounds checking. Dynamic derivatives are manusl output for aircraft that have wings that are not straight-tapered or have leading edge extensions.
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. There is no method to input twin vertical tails mounted on the fuselage, although there is a method for H-Tails.