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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Retrieved from ” https: The X- and Z- coordinates are needed for the winghorizontal tailand vertical tail in order for the aircraft to be synthesized correctly. This classification is summarized below:. Views Read Edit View history.
The United States Air Force Stability and Control DATCOM is a collection, correlation, codification, and recording of best knowledge, opinion, and judgment dtcom the area of aerodynamic stability and control prediction methods. The basic parameters such as root chord, tip chord, half-span, twistdihedral and sweep are input.
Additional Engineering References Bruhn: The automated translation of this page is provided by a general datccom third party translator tool. From Wikipedia, the free encyclopedia.
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United States Air Force Stability and Control Digital DATCOM
ysaf Drag of two-dimensional steps and ridges in a turbulent boundary layer for Mach numbers up to 3 Flight Sciences: 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.
This page has been translated by MathWorks. Fundamentally, the purpose of the DATCOM Data Compendiumis to provide a systematic summary of methods for estimating basic stability and control derivatives. Up to 20 stations can be specified with the fuselage half-width, upper coordinate and lower coordinate being defined at each station.
United States Air Force Stability and Control Digital DATCOM – Wikipedia
Up to 9 flap deflections can be analyzed at each Mach-altitude combination. For complete aircraft configurations, downwash data is also included. There has been some research in using Digital DATCOM in conjunction with wind tunnel studies to predict aerodynamics of structurally impaired aircraft. This Collection contains the following information.
The book is intended to be used for preliminary design purposes before the acquisition of test data.
From Wikipedia, the free encyclopedia. However, in its day, the program was an advanced estimation tool, and certainly much faster than plowing through pages and pages of engineering texts.
All Examples Functions More. For supersonic analysis, additional parameters can be input. The canard must be specified as the forward lifting surface i.
Importing from USAF Digital DATCOM Files – MATLAB & Simulink – MathWorks Deutschland
The report consists of.
The methodology can be used to quickly generate aerodynamic model for damaged aircraft for simulation and reconfigurable control. This classification is summarized below: A spectrum of methods is presented, ranging from very simple and easily applied techniques to quite accurate and thorough procedures.
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.
DATCOM provides a systematic summary of methods for estimating basic stability and control derivatives. It bridges the gap between theory and practice by including a combination of pertinent discussion and proven practical methods. For any given configuration and flight condition, a complete set of stability and control derivatives can be determined without resort to outside information.
Wing lift-curve slope Local and mean skin friction coefficients on a flat plate Aerospace Structures: 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. Explore the A-Z Index.
This problem can be addressed by approximating the twin vertical tails as a single equivalent vertical tail mounted to the fuselage.