Site Loader

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.

Author: Zulkiran Vobei
Country: Burkina Faso
Language: English (Spanish)
Genre: Love
Published (Last): 20 October 2014
Pages: 227
PDF File Size: 9.31 Mb
ePub File Size: 8.72 Mb
ISBN: 830-4-71559-968-2
Downloads: 71597
Price: Free* [*Free Regsitration Required]
Uploader: Vunris

Views Read Edit View history.

Data tables can easily be output to the screen or to PNG files for inclusion into reports. The new input file format allows the user to place comments in the input file. The user can specify whether the Mach number and altitude varies together, the Mach number varies at a constant altitude, or the altitude varies manjal a constant Mach number.

Printed Manuals for USAF Datcom

Articles lacking in-text citations from March All articles lacking in-text citations. The basic parameters such as root chord, tip chord, half-span, twistdihedral and sweep are input. For complete aircraft configurations, downwash data is also included.

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.

An alpha version of the program was released November 1, to the general public.

USAF Digital Datcom

This problem can be addressed by superposition of lifting surfaces through the experimental input option. The canard must be specified as the forward lifting surface i. Up to 9 flap deflections can be analyzed at each Mach-altitude combination. Up to 20 stations can be specified with the fuselage half-width, upper coordinate and lower coordinate being defined at each station.


There has been some research in using Digital DATCOM in conjunction with wind tunnel studies to predict aerodynamics of structurally impaired aircraft. Please help to improve this article by introducing more precise citations. 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.

Digital Datcom

The X- and Z- coordinates are needed for the winghorizontal tailand vertical tail in order for the aircraft to be synthesized correctly. Dynamic derivatives are not output for aircraft that have wings that are not straight-tapered or have leading edge extensions.

From Datcm, the free encyclopedia. According to the manual, there is no any input parameters which define the geometriy of rudder. By using this site, you agree to the Terms of Use and Privacy Policy.

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.

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 report consists of. For each configuration, stability coefficients and derivatives are output at each angle of attack specified.

The methodology can be used to quickly generate aerodynamic model for damaged aircraft for simulation and reconfigurable control.


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 Additionally, custom airfoils can be input using the appropriate namelists. This problem can be overcome by using experimental data for the wing-body using non-straight tapered wing.


For supersonic analysis, additional parameters can be input. All dimensions are taken in feet and degrees unless specified otherwise. Incidence angles can also be added to the wing and horizontal tail. There is no method to input twin vertical tails mounted on the fuselage, although there is a method for H-Tails. Retrieved from ” https: This problem can be addressed by approximating the twin vertical tails as a single equivalent vertical tail mounted to the fuselage. The simplification affects the coefficient of drag for the aircraft.

However, in its day, the program was an advanced estimation tool, and certainly much faster than plowing through pages and pages of engineering texts. This article includes a list of referencesbut its sources remain unclear because it has insufficient inline citations.

A maximum of Mach-altitude combinations can be run at once, with up to 20 angles of attack for each combination. Three damage-configurations are studied at supersonic speeds.

OpenDatcom incorporates all the basic non-experimental functionality supported by the Digital DATCOM while providing real-time input error and bounds checking.