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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Up to 9 flap deflections can be analyzed at each Mach-altitude combination. For complete aircraft configurations, downwash data is also included.
However, in its day, the program was an advanced estimation tool, and certainly much faster than plowing through pages and pages of engineering texts. 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.
The basic parameters such as root chord, tip chord, half-span, twistdihedral and sweep are input. A maximum of Mach-altitude combinations can be run at once, with up to 20 angles of attack for each combination. Digital DATCOM requires an input file containing a geometric description of an aircraft, and outputs its corresponding dimensionless stability derivatives according to the mqnual flight conditions. 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.
The report consists of. Retrieved from ” https: There have ddatcom 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.
According to the manual, there is no any input parameters which define the geometriy of rudder. Three damage-configurations are studied at supersonic speeds. 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.
USAF Digital Datcom
The basic output includes:. The methodology can be used to quickly generate aerodynamic model for damaged aircraft for simulation and reconfigurable control.
The canard must be specified as the forward lifting surface i. Articles lacking in-text citations from March All articles lacking in-text citations. 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.
The X- and Dqtcom coordinates are needed for the winghorizontal tailand vertical tail in order for the aircraft to be synthesized correctly. By default, only the data for the aircraft is output, but additional configurations can be output:.
Printed Manuals for the USAF Datcom
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. Please help to improve this article by introducing more precise citations. The simplification affects the coefficient of drag for the aircraft.
Up to 20 stations can be specified with the fuselage half-width, manuual 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.
The theoretical wing area, mean aerodynamic chordand wing span are input along with a parameter defining the surface roughness of the aircraft. This problem can be overcome by using experimental data for the wing-body using non-straight tapered wing. This article includes a list of referencesbut its sources remain unclear because it has insufficient inline citations.
Additionally, custom airfoils can be input using the appropriate namelists. This page was last edited on 22 Decemberat Dynamic derivatives are not output for aircraft that have wings that are not straight-tapered or have leading edge extensions.
The values obtained can be used to calculate meaningful aspects datco, flight dynamics. 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.
March Learn how and when to remove this template message. Views Read Edit View history. For each configuration, stability coefficients and derivatives are output at each angle of attack specified.
This problem can be addressed by superposition of lifting surfaces through the experimental input option.
Incidence angles can datclm be added to the wing and horizontal tail. An alpha version of the program was released November 1, to the general public. Data tables can easily be output to the screen or to PNG files for inclusion into reports. While the original DIGDAT program has manyal 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 This problem can be addressed by approximating the twin vertical tails as a single equivalent vertical tail mounted to the fuselage.
All dimensions are taken in feet and degrees unless specified otherwise. For supersonic analysis, additional parameters can be input.