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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For each configuration, stability coefficients and derivatives are output at each angle of attack specified. 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. 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.
The report consists of. 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. This problem can be addressed by superposition of lifting surfaces through the experimental input option.
For supersonic analysis, additional parameters can be input. This problem can be addressed by approximating the twin vertical tails as a single equivalent vertical tail mounted to the fuselage. Dynamic derivatives are not 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.
USAF Digital 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.
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 Views Read Edit View history. The new daycom file format allows the user to place comments in the input file.
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 manuzl the data into another application.
This page was last edited on 22 Decemberat The simplification affects the coefficient of drag for the aircraft.
Printed Manuals for the USAF Datcom
From Wikipedia, the free encyclopedia. The theoretical wing area, mean aerodynamic chordand wing span are input along with a parameter defining the surface roughness of the aircraft. Articles lacking in-text citations from March All articles lacking in-text citations. This problem can be overcome by using experimental data for the wing-body using non-straight tapered wing. The methodology can be used to quickly generate mznual model for damaged aircraft manuall simulation and reconfigurable control.
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.
The basic parameters such as root chord, tip chord, half-span, twistdihedral and sweep are input. 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. Manuaal to 20 stations can be specified with the fuselage half-width, upper coordinate and lower coordinate being defined at daycom station.
The canard must be specified as the forward lifting surface i. This article includes a list of referencesbut its sources remain unclear because it has insufficient inline citations.
Datco tables can easily be output to the screen or to PNG files for inclusion into reports. Retrieved from ” https: The X- and Z- coordinates are needed for the winghorizontal tailand vertical tail in order for the aircraft to be synthesized correctly. All dimensions are taken in feet and degrees unless specified otherwise. The values obtained can be manula to calculate meaningful aspects of flight dynamics. An alpha version of the program was released November 1, to the general public.
Up to 9 flap deflections can be analyzed at each Mach-altitude combination. March Learn how and when to remove this template message.
The basic output includes:. Additionally, custom airfoils can be input using the appropriate namelists. Incidence angles can also be added to the wing and horizontal tail.
For complete aircraft configurations, downwash data is also included. Datclm incorporates all the basic non-experimental functionality supported by the Digital DATCOM while providing real-time input error and bounds checking.
According to the manual, there is no any input parameters which define the geometriy of rudder.