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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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.

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

March Learn how and when to remove this template message. There has been some research in using Digital DATCOM in conjunction with wind tunnel studies to predict aerodynamics of structurally impaired aircraft. This page was last edited on 22 Decemberat An alpha version of the program was released November 1, to the general public. However, datcon its day, the program was an manuaal estimation tool, and certainly much faster than plowing through pages and pages of engineering texts.

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The report consists of.

USAF Digital Datcom

Up to 9 flap deflections can be analyzed at each Mach-altitude combination. 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.

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 values obtained can be used to calculate meaningful datcomm of flight dynamics.

United States Air Force Stability and Control Digital DATCOM

For complete aircraft configurations, downwash data is also included. Additionally, custom airfoils can be input using the appropriate namelists.

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. Views Read Edit View history. Dynamic derivatives are not output for aircraft that have wings that are not straight-tapered or have leading edge extensions. While the original DIGDAT program has been left relatively untouched, there has been a new front-end created that will allow the user dafcom name the input file with something more significant than FOR 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. 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. This problem can be addressed by approximating the twin vertical tails as a single equivalent vertical tail mounted to the fuselage.

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

By using this site, you agree to the Terms of Use and Privacy Policy. There is manuao method to input twin vertical tails mounted on the fuselage, although there is a method for H-Tails. Articles lacking in-text citations from March All articles lacking in-text citations. There are intentions dtcom those that use this package to improve the overall package, through an easier user interface, as well as more comprehensive output data. According to the manual, there is no any input parameters which define the geometriy of rudder.

United States Air Force Stability and Control Digital DATCOM – Wikipedia

This problem can be addressed by superposition of lifting surfaces through the experimental input option. Please help to improve this article by introducing more precise citations. All dimensions are taken in feet and degrees unless specified otherwise. Incidence angles xatcom also be added to the wing and horizontal tail.

The simplification affects the coefficient of drag for the aircraft.