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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Comparatively simple methods are presented in complete form, while the more complex methods are often handled by reference to separate treatments. Finck, R D Full Text: Tables which compare calculated results with test data provide indications of uswf accuracy.
A spectrum of methods is presented, ranging from very simple and easily applied techniques to quite accurate and thorough procedures.
Additionally, custom airfoils can be input using the appropriate namelists.
By default, only the data for the aircraft is output, but additional configurations can be output:. All Examples Functions More. Wing lift-curve slope Local and mean skin friction coefficients on a flat plate Aerospace Structures: 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 DATCOM provides a systematic summary of methods for estimating basic stability and control derivatives.
Select a Web Site Choose a web site to get translated content where available and see local events and offers. This article includes a list of referencesbut its sources remain unclear because it has insufficient inline citations. The book is intended to be used for preliminary design purposes before the acquisition of test data.
Tables which compare calculated results with test data provide indications of method accuracy. Incidence angles can also be added to the wing and horizontal tail. This page was last edited on 14 Mayat Summary Table of Contents.
Additional Engineering References Bruhn: The automated translation of this page is provided by a general purpose third party translator tool. The canard must be specified as the forward lifting surface i. Please help to improve this article by introducing more precise citations.
There are intentions among those that use this package to improve the overall package, through an easier user interface, as well as more comprehensive output data.
For any given flight condition and configuration the complete set of derivatives can be determined without resort to outside information. Views Read Edit View history. OpenDatcom incorporates all the basic non-experimental functionality supported by the Digital DATCOM while providing real-time input error and bounds checking.
United States Air Force Stability and Control Digital DATCOM
Fundamentally, the purpose of the DATCOM Data Compendiumis to provide a systematic summary of methods for estimating basic stability and control derivatives. From Wikipedia, the free encyclopedia. It bridges the gap between theory usxf practice by including a combination of pertinent discussion and proven practical methods. The methodology can be used to quickly generate aerodynamic model for damaged aircraft for simulation and reconfigurable control.
All dimensions are taken in feet and degrees unless specified otherwise. This problem can be addressed by superposition of lifting surfaces through the experimental input option.
According to the manual, there is no any input parameters which define the geometriy of rudder. Extensive references to related material are also included. 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
The report consists of. Fluid Mechanics Distribution Statement: This Collection contains the following information.
The X- and Z- coordinates are needed for the winghorizontal tailand vertical tail in order for the aircraft to be synthesized correctly. This page was last edited on 22 Decemberat International Standard Atmosphere TM Extensive references to related material are also included.
Choose a web site to get translated content where available and see local events and offers. It presents substantiated techniques for use 1 early in the design or concept study phase, 2 to evaluate changes resulting from proposed engineering fixes, and 3 as a training on crosstraining aid. Drag of two-dimensional steps and ridges in a turbulent boundary layer for Mach numbers up to 3 Flight Sciences: 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.
Click the button below to return to the English version of the page. For complete aircraft configurations, downwash data is also included. However, in its day, the program was an advanced estimation tool, and certainly much faster than plowing through pages and pages of engineering texts. This problem can be overcome by using experimental data for the wing-body using non-straight tapered wing. 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 uaf 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.