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 complete aircraft configurations, downwash data is also included.

Please help to improve nanual article by introducing more precise citations. Dynamic derivatives are not output for aircraft that have wings that are not straight-tapered or have leading edge extensions.

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

The report consists of.

United States Air Force Stability and Control Digital DATCOM

Articles lacking in-text citations from March All articles lacking in-text citations. The simplification affects the coefficient of drag for the aircraft. There are intentions among those that use this package to improve the overall package, through an easier user interface, as well as more datcm output data.

Digital DATCOM requires manuxl input file containing a geometric description of an aircraft, and outputs its corresponding dimensionless stability derivatives according to the specified flight conditions. 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.

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Printed Manuals for the USAF Datcom

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

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

For supersonic analysis, additional parameters can be input. A maximum of Mach-altitude combinations can be run at once, with up to 20 angles of attack for each combination. All dimensions are taken in feet and degrees unless specified otherwise.

From Wikipedia, the free encyclopedia. Manaul basic parameters such as root chord, tip chord, half-span, twistdihedral and sweep are input.

Up to 9 flap deflections can be analyzed at each Mach-altitude combination. There has been some research in using Digital DATCOM in conjunction with wind tunnel studies to predict aerodynamics of structurally impaired aircraft. The X- and Z- coordinates are needed for the winghorizontal tailand vertical tail in order for the aircraft to be synthesized correctly.

An alpha mannual of the program was released November 1, to the general public. By using this site, you agree to the Terms of Use and Privacy Policy. While the original DIGDAT program datcpm been left relatively untouched, there has been a new front-end created that will allow datcomm user to name the input file with something more significant than FOR OpenDatcom incorporates all the basic non-experimental functionality supported by the Digital DATCOM while providing real-time input error and bounds checking.

USAF Digital Datcom

The values obtained can be used to calculate meaningful aspects of flight dynamics. Retrieved from ” https: 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. The theoretical wing area, mean aerodynamic chordand wing span are input along with a parameter defining the surface roughness of the aircraft. 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.

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This page was last edited on 22 Decemberat Up to 20 stations can be specified with the fuselage half-width, upper coordinate and lower coordinate being defined at each station.

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. Data tables can easily be output to the screen or to PNG files for inclusion into reports.

Additionally, custom airfoils manhal be input using the appropriate namelists. This article includes a list of referencesbut its sources remain unclear because it has insufficient inline citations. 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 problem can be addressed by superposition of lifting surfaces through the experimental input option. Views Read Edit View history.