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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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.
The dattcom affects the coefficient of drag for the aircraft. The basic parameters such as root chord, tip chord, half-span, twistdihedral and sweep are input. Retrieved from manusl https: A new methodology is then proposed which combines the experimental results of healthy aircraft with the darcom aerodynamics of the damaged cases, to yield better correlation between experimental and predicted aerodynamic coefficients for damaged aircraft.
The new input file format allows the user to place comments in the input file. Incidence angles can also be added to the wing and horizontal tail. 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.
For supersonic analysis, additional parameters can be input. ,anual report consists of. An alpha version of the program was released November 1, to the general public.
The theoretical wing area, mean aerodynamic chordand wing span are input along with a parameter defining the surface roughness of the aircraft. Please help to improve this article by introducing more precise citations.
Printed Manuals for USAF Datcom
By default, only the data for the aircraft is output, but additional configurations can be output:. There is no method to input twin vertical tails mounted on the fuselage, although there is a method for H-Tails. OpenDatcom incorporates all the basic non-experimental functionality supported by the Digital DATCOM while providing real-time input error and bounds checking.
March Learn how and when to remove this template message. Additionally, custom airfoils can be input using the appropriate namelists. A maximum of Mach-altitude combinations can be run at once, with up to 20 angles of attack for each combination.
The basic output includes:. This page was last edited on 22 Decemberat The X- and Z- coordinates are needed for the winghorizontal tailand vertical tail in order for the aircraft to be synthesized correctly. Data tables can easily be output to the dstcom or to PNG files for inclusion into reports.
For complete aircraft configurations, downwash data is also included. This article includes a list of referencesbut its sources remain unclear because it has insufficient inline citations. According to the manual, there is no any input parameters which define the geometriy of rudder.
Articles lacking in-text citations from March All articles lacking in-text citations. 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.
There has been some research in using Digital Datclm in conjunction with wind tunnel studies to predict aerodynamics of structurally impaired aircraft.
From Wikipedia, the free encyclopedia. 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. For each configuration, stability coefficients and derivatives are output at each angle of attack specified.
Views Read Edit View history. The canard must be specified as the forward lifting surface i. This problem can be addressed by superposition of lifting surfaces through the adtcom input option. 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. Three damage-configurations are studied at supersonic speeds.
However, in its day, the program was an advanced estimation tool, and certainly much faster than plowing through pages and pages of engineering texts. The values obtained can be used to calculate meaningful aspects of flight dynamics.
All dimensions are taken in feet and degrees unless specified otherwise. This problem can be overcome by using experimental data for the wing-body using non-straight tapered wing. Up to 20 stations can be specified with the fuselage half-width, upper coordinate and lower coordinate being defined at each station. Up to 9 flap deflections can be analyzed at each Mach-altitude combination.
Dynamic derivatives are not output for aircraft that have wings that are not straight-tapered or have leading edge extensions. 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