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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All dimensions are taken in feet and degrees unless specified otherwise.
Data tables can easily be output to the screen or to PNG files for inclusion into reports. The X- and Z- coordinates are needed for the winghorizontal tailand vertical tail in order for the aircraft to be synthesized correctly. Up to 9 flap deflections can be analyzed at each Mach-altitude combination.
For supersonic analysis, additional parameters can be input. The canard must be specified amnual the forward lifting maunal i. Up to 20 stations can be specified with the fuselage half-width, upper coordinate and lower coordinate being defined at each station.
United States Air Force Stability and Control Digital DATCOM
There is no method to input twin vertical tails mounted on the fuselage, although there is a method for H-Tails. 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.
Raw results from the code provide good correlation with wind tunnel data at very low angles maunal 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 complete aircraft configurations, downwash data is also included.
The new input file format allows the user to place comments in the input file. This problem can be addressed by superposition of lifting surfaces through the manyal input option.
Incidence angles can also be added to the wing and horizontal tail. Additionally, custom airfoils can be input using the appropriate namelists.
Articles lacking in-text citations from March All articles lacking in-text citations. 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. DATCOM does not require that the origin for the aircraft has to be the nose of the aircraft; any manusl point will do, but all of the dimensions need to be referenced from that point.
An alpha version of the program was released November 1, to the general public.
United States Air Force Stability and Control Digital DATCOM – Wikipedia
The values obtained can be used to calculate meaningful aspects of flight dynamics. Dynamic derivatives are not output for aircraft that have wings that are not straight-tapered or have leading edge extensions. The basic output includes:. The report consists of. OpenDatcom incorporates all the basic non-experimental functionality supported by the Digital DATCOM while providing real-time input error and bounds checking.
This problem can be overcome by using experimental data for 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. A maximum of Mach-altitude combinations can be run at once, with up to 20 angles of attack for each combination.
There has been some research in using Digital DATCOM in conjunction with wind tunnel studies to predict aerodynamics of structurally impaired aircraft.
Three damage-configurations are studied at supersonic speeds. For each configuration, stability coefficients and derivatives are output at each angle of attack specified.
Printed Manuals for USAF Datcom
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 basic parameters such as root chord, tip chord, half-span, twistdihedral and sweep are input. The simplification affects the coefficient of drag for the aircraft.
Please help to improve this article by introducing more precise citations. This page was last edited on 22 Decemberat However, in its day, the program was janual advanced estimation tool, and certainly much faster than plowing through pages and pages of engineering texts.
This problem can be addressed by approximating the twin vertical tails as a single equivalent vertical tail mounted to the fuselage.
Printed Manuals for the USAF Datcom
This article includes a list of referencesbut its sources remain unclear because it has insufficient inline citations. From Wikipedia, the free encyclopedia. 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.
Views Read Dagcom View history. The methodology can be used to quickly generate aerodynamic model for damaged aircraft for simulation and reconfigurable control. 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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