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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The X- and Z- coordinates are needed for the winghorizontal tailand vertical tail in order for the aircraft to be synthesized correctly. This problem can be addressed by superposition of lifting surfaces through the experimental input option.

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. 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.

Up to 9 flap deflections can be analyzed at each Mach-altitude combination. 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. Retrieved from ” https: From Wikipedia, the free encyclopedia.

By default, only the data for the aircraft is output, but additional configurations can be output:.

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. 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 DATCOM in conjunction with wind tunnel studies to predict aerodynamics of structurally impaired aircraft. The basic output includes:. The basic parameters such as root chord, tip chord, half-span, twistdihedral and sweep are input.

Views Read Edit View history. Articles lacking in-text citations from March All mxnual lacking in-text citations. 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 By using this site, you agree to the Terms of Use and Privacy Policy.

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.

An alpha version of the program was released November 1, to the general public. The new input file format allows the user to place comments in the input file. Three damage-configurations are studied at supersonic speeds.

This page was last edited on 22 Decemberat According to the manual, there is no any input parameters which define the geometriy of rudder.

All dimensions are taken in feet and degrees unless specified otherwise. Please help to improve mnaual article by introducing more precise citations.


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.

Datxom, in its day, the program was an advanced estimation tool, and certainly much faster than plowing through pages and pages of engineering texts. There is no method to input twin vertical tails mounted on the fuselage, although there is a method for H-Tails. The methodology can be used to quickly generate aerodynamic model for damaged aircraft for simulation and reconfigurable control.

For supersonic analysis, additional parameters can be input. March Learn how and when to remove this template message. This article includes a list of referencesbut its sources remain unclear because it has insufficient inline citations. For each configuration, stability coefficients and derivatives are output at each angle of attack specified. The values obtained can be used to calculate meaningful aspects of flight dynamics.

USAF Digital Datcom

datckm The canard must be specified as the forward lifting surface i. The theoretical wing area, mean aerodynamic chordand wing span are input along with a parameter defining the surface roughness of the aircraft. A maximum of Mach-altitude combinations can be run at once, with up to 20 angles of attack for each combination. The report consists of. Incidence angles can also be added to the wing and horizontal tail.

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