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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A maximum of Mach-altitude combinations can be run at once, with up to 20 angles of attack for each combination.

This page was last edited on 22 Decemberat The theoretical wing area, mean aerodynamic chordand wing span are input along with a parameter defining the surface roughness of the aircraft.

Views Read Edit View history. All dimensions are taken in feet amnual degrees unless specified otherwise. Up to 9 flap deflections can be datcoj at each Mach-altitude combination. The canard must be specified as the forward lifting surface i.

The simplification affects the coefficient of drag for the aircraft. This article includes a list of referencesbut its sources remain unclear because it has insufficient inline citations. The values obtained can be used to calculate meaningful aspects of manjal dynamics.

This problem can be addressed by approximating the twin vertical tails as a single equivalent vertical tail mounted to the fuselage.

Additionally, custom airfoils can be input using the appropriate namelists. The basic output includes:. For supersonic analysis, additional parameters can be input.

Digital Datcom

Articles lacking in-text citations from March All articles lacking in-text citations. An alpha version of the program was released November 1, to the general public. Retrieved from ” https: For complete aircraft configurations, downwash data is also included.

Incidence angles can also be added to the wing and horizontal tail. OpenDatcom incorporates all the basic non-experimental functionality supported by the Digital DATCOM while providing real-time input error and bounds checking.

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March Learn how and when to remove this template message. There is no method to input twin vertical tails mounted on the fuselage, although there is a method for H-Tails. This problem can be overcome by using experimental data for the wing-body using non-straight tapered wing. 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. Data tables can easily be output to the screen or to PNG files for inclusion into reports.

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. Three damage-configurations are studied at supersonic speeds. 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 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.

Please help to improve this article by introducing more precise citations.

Printed Manuals for the USAF Datcom

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

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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.

The new input file format allows the user to place comments in the input file. The methodology can be used to quickly generate aerodynamic model for damaged aircraft for simulation and reconfigurable control.

The basic parameters such as root chord, tip chord, half-span, twistdihedral and sweep are input.

Up to 20 stations can be specified with the fuselage half-width, upper coordinate and lower coordinate being defined datom each station.

This problem can be addressed by superposition of lifting surfaces through the experimental input option. The report consists of. For each configuration, stability coefficients and derivatives are output at each angle of attack specified.

Printed Manuals for USAF Datcom

By default, only the data for the aircraft is output, but additional configurations can be output:. DATCOM does not require that the origin for mabual aircraft has to be the nose majual the aircraft; any arbitrary point will do, but all of the dimensions need to be referenced from that point. However, in its day, the program was an advanced estimation tool, and certainly much faster than plowing through pages and pages of engineering texts.

By using this site, you agree to the Terms of Use and Privacy Policy. There has been some research in using Digital DATCOM in conjunction with wind tunnel studies to predict aerodynamics of structurally impaired aircraft.