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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Printed Manuals for the USAF Datcom
For supersonic analysis, additional parameters can be input. Dynamic derivatives are not output for aircraft that have wings that are not straight-tapered or have leading edge extensions. This article includes a list of referencesbut its sources remain unclear because it has mamual inline citations. Views Read Edit View history. This problem can be overcome by using experimental data for the wing-body using non-straight tapered wing. Retrieved from datcok https: There has been some research in using Digital DATCOM in conjunction with wind tunnel studies to predict aerodynamics of structurally impaired aircraft.
Three damage-configurations are studied at supersonic speeds. By using this site, you agree to the Terms of Use and Privacy Msnual. The theoretical wing area, mean aerodynamic chordand wing span are input along with a parameter defining the surface roughness of the aircraft.
Please help to improve this article by introducing more precise 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. Incidence angles can also be added to the wing and horizontal tail. Data tables can easily be output to the screen or to PNG files for inclusion into reports. 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 vatcom something manhal significant than FOR March Learn how and when to remove this template message.

The report consists of. 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. According to the manual, there is no any input parameters which define the geometriy of rudder.
USAF Digital Datcom
The X- and Z- coordinates are needed for the winghorizontal tailand vertical tail in order for the aircraft to be synthesized correctly. Datcomm 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. Articles lacking in-text citations from March All articles lacking in-text citations.
The canard must be specified as the forward lifting surface i. Up to 20 stations can be specified with the fuselage half-width, upper coordinate and lower coordinate being defined at each station. This problem can be addressed by approximating the twin vertical tails as a single equivalent vertical tail mounted to the fuselage.
The new input file format allows the user to place comments in the input file. The basic parameters such as root chord, tip chord, half-span, twistdihedral and sweep are input. The methodology can be used to quickly generate aerodynamic model for damaged aircraft for simulation and reconfigurable control. For complete aircraft configurations, downwash data is also included. An alpha version of the program was released November 1, to the general public.
The basic output includes:. This problem can be addressed by superposition of lifting surfaces through the experimental input option. For each configuration, stability coefficients and derivatives are output at each angle of attack specified. Additionally, custom airfoils can be input using the appropriate namelists.

This page was last edited on 22 Decemberat From Wikipedia, the free encyclopedia. Up to 9 flap deflections can be analyzed at each Mach-altitude combination. A maximum of Mach-altitude combinations can be run at once, with up to 20 angles of attack for each combination.
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 manul stability derivatives according to the specified flight conditions.
