tions 4 through 7 of the USAF Stability and Control Datcom (revised April. ). The report consists of the following three volumes: o Volume I, Users Manual. This report is a collection, correlation, codification, and recording of best knowledge, opinion, and judgment in the area of aerodynamic stability and control. contract FC, which automated Sections 4 and 5 of the USAF Sta- bility and Control Datcom; AFFDL TR produced under contract.
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The new input file format allows the user to place comments in the input file. Select the China site dztcom Chinese or English for best site performance. 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. 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.
The book is intended to be used for preliminary design purposes before the acquisition of test data. The missing data points will be filled with the values for the first alpha, since these data points are meant to be used for all alpha values.
Summary Table of Contents.
USAF Stability and Control DATCOM – Wikipedia
The automated translation of this page is provided by a general purpose third party translator tool. Translated by Mouseover text to see original. However, in its day, the program was an advanced estimation tool, and certainly much faster than plowing through pages and pages of engineering texts.
The methodology can be used to quickly generate aerodynamic model for damaged aircraft for dactom and reconfigurable control. This problem can be overcome by using experimental data for the wing-body using non-straight tapered wing.
From Wikipedia, the free encyclopedia. Extensive references to related material are also included. A spectrum of methods is presented, ranging from very simple uaf easily applied techniques to quite accurate and thorough procedures. They also provide a possible resource in areas not currently covered by ESDU.
A spectrum of methods is presented, ranging from very simple and easily applied techniques to quite accurate and thorough usac. Comparatively simple methods are presented in complete form, while the more complex methods are often handled by reference to separate treatments.
This report is a collection, correlation, codification, and recording of best knowledge, opinion, and judgment in the area of aerodynamic stability and control prediction methods. An alpha version of the program was released November 1, to the general public.
Datdom incorporates all the basic non-experimental functionality supported by the Digital DATCOM while providing real-time input error and bounds checking.
Fluid Mechanics Distribution Statement: The United States Air Force Stability and Control DATCOM is a collection, correlation, codification, and recording of best knowledge, opinion, and judgment in the area of aerodynamic stability and control prediction methods. For any given configuration and flight condition, a complete set of stability and control derivatives can be determined without resort to outside information. Finck, R D Full Text: Select a Web Site Choose a web site to get translated content where available and see local events and offers.
All Examples Functions More. There are datckm among those that use this package to improve the overall package, through an easier user interface, as well as more comprehensive output data.
Articles lacking in-text citations from March All articles lacking in-text citations. Toolbox Toolbox home Aerodynamics: International Standard Atmosphere TM Extensive references to related material are also included.
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. Comparatively simple methods are presented in complete form, while the more complex methods are often handled by reference to separate treatments.
This Collection contains the following information. MathWorks does not warrant, and disclaims all liability for, the accuracy, suitability, or fitness for purpose of the translation. By default, only the data for the aircraft is output, but additional configurations can be output:. The simplification affects the coefficient of drag for the aircraft. Additionally, custom airfoils can be input using the appropriate namelists. If wing-alone test data are available, it is obvious that these test data should be substituted in place of the estimated wing-alone characteristics in determining the lift-curve slope of the combination.
Drag due to a circular cavity in a plate with turbulent boundary layer at subsonic, transonic or supersonic speeds A Explore the A-Z Index. Tables which compare calculated results with test data provide indications of method accuracy.
There usaaf been some research in using Digital DATCOM in conjunction with wind tunnel studies to predict aerodynamics of structurally impaired aircraft. For any given configuration and flight condition, a complete set of stability and control derivatives can be determined without resort to outside information.
United States Air Force Stability and Control Digital DATCOM
This page has been translated by MathWorks. The canard must be specified as the forward lifting surface i. 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.
Dynamic derivatives are not output for aircraft that have wings that are not straight-tapered or have leading edge extensions. The book is intended to be used for preliminary design purposes before the acquisition of test data. Retrieved from ” https: March Learn how and when to remove this template message. A spectrum of methods is presented, ranging from very simple and easily applied techniques to quite accurate and thorough procedures.
The values obtained can be used to calculate meaningful aspects of flight dynamics. Data tables can easily be output to the screen or to PNG files for inclusion into reports.