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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For any given configuration and flight condition, a complete set of stability and control derivatives can be determined without resort to outside information.
The simplification affects the coefficient of drag for the aircraft. Additionally, custom airfoils can be input using the appropriate namelists. Toolbox Toolbox home Aerodynamics: Click the button below to return to the English version of the page.
Comparatively simple methods are presented in complete form, while the more complex methods are often handled by reference to separate treatments. Translated by Mouseover text to see original. Sep Sep Corporate Author: There are intentions datcok those that use this package to improve the overall package, through an easier user interface, as well as more comprehensive output data.
USAF Stability and Control DATCOM
A new methodology is then proposed which combines the experimental results of healthy aircraft with the predicted aerodynamics of the uaf cases, to yield better correlation between experimental and predicted aerodynamic coefficients for damaged aircraft. Extensive references to datcmo material are also included. Incidence angles can also be added to the wing and horizontal tail. From Wikipedia, the free encyclopedia.
For instance, if the lift-curve slope of a wing-body combination is desired, the DATCOM recommends that the lift-curve slopes of the isolated wing and body, respectively, be estimated by methods presented and that appropriate wing-body interference factors also presented be applied. Extensive references to related material are also included.
March Learn how and when to remove this template message. DATCOM provides a systematic summary of methods for estimating basic stability and control derivatives.
This classification is summarized below: Summary Table of Contents.
The basic parameters such as root chord, tip chord, half-span, twistdihedral and sweep are input. The book is intended to be used for preliminary design purposes before the acquisition of test data. Data tables can easily be output to the screen or to PNG files for inclusion into reports.
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All Examples Functions More. Views Read Edit View history. The United States Air Force Stability and Control Datcim is a collection, correlation, codification, and recording of best knowledge, opinion, and judgment in the area of aerodynamic stability and control prediction methods.
This Collection contains the following information. Comparatively simple methods are presented in complete form, while the more complex methods are often handled by reference to separate treatments.
USAF Stability and Control DATCOM – Wikipedia
Click here to see To view all translated materials including this page, select Country from the country navigator on the bottom of this page. The report consists of.
Drag of two-dimensional steps and ridges in a turbulent boundary layer for Mach numbers up to 3 Flight Sciences: This problem can be addressed by approximating the twin vertical tails as a single equivalent vertical tail mounted to the fuselage. 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.
Based datcim your location, we recommend that you select: MathWorks does not warrant, and disclaims all liability for, the accuracy, suitability, or fitness for purpose of the translation. 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.
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 with something more significant than FOR The missing data points will be filled with the values for usxf first alpha, since these data points are meant to be used for all alpha values. The values obtained can be used to calculate meaningful aspects of flight dynamics.
A spectrum of methods is presented, ranging from very simple and easily applied techniques to quite accurate and thorough procedures. This page was last edited on 22 Decemberat The methodology can be used to quickly generate aerodynamic model for damaged aircraft for simulation and reconfigurable control. According to the manual, there is no any input parameters which define the geometriy of rudder.
Drag due to a circular cavity in a plate with turbulent boundary layer at subsonic, transonic or supersonic speeds A The X- and Z- coordinates are needed for the winghorizontal tailand vertical tail ksaf order for the aircraft to be synthesized correctly. For supersonic analysis, additional parameters can be input.
Three damage-configurations are studied at supersonic speeds. This classification is summarized below:. There is no method to input twin vertical tails mounted on the fuselage, although there is a method for H-Tails.