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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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. A spectrum of methods is presented, ranging from very simple and easily applied techniques to quite accurate and thorough procedures. Additional Engineering References Bruhn: DATCOM does not require that the origin for the aircraft has to be the nose of darcom aircraft; any arbitrary ddatcom will do, but all of the dimensions need to be referenced from that point.
All Examples Functions More. For complete aircraft configurations, downwash data is also included. 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. Additionally, custom airfoils can be input using the appropriate namelists. For supersonic analysis, additional parameters can be input. Up to 20 stations can be specified with the fuselage half-width, upper coordinate and lower coordinate being defined at each station.
A spectrum of methods is presented, ranging from very simple and easily applied techniques to quite accurate and thorough procedures. 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 article includes a list of referencesbut its sources remain unclear because it has insufficient inline citations. The methodology can be used to quickly generate aerodynamic model for damaged aircraft uasf simulation and reconfigurable control. Views Read Edit View history. 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.
This is machine translation Translated by. 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 the first alpha, since these data points are meant to be used daycom all alpha values.
Extensive references to related material are also included. There has been some research in using Digital DATCOM in conjunction with wind tunnel studies to predict aerodynamics of structurally impaired aircraft.
Drag of two-dimensional steps and ridges in a turbulent boundary layer for Mach numbers up to 3 Flight Sciences: Extensive references to related material are also included. Incidence angles can also be added to the wing and horizontal tail.
IHS ESDU: USAF DATCOM
A maximum of Mach-altitude combinations can be run at once, with up to 20 angles of attack for each combination. Drag due to grooves in a flat plate with a turbulent boundary layer, at subsonic and supersonic speeds A Retrieved from ” https: 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 cross-training aid. The basic parameters such as root chord, tip chord, half-span, twistdihedral and sweep are input.
By default, only the data for the aircraft is output, but additional configurations can be output:. Comparatively simple methods are presented in complete form, while the more complex methods are often handled by reference to separate treatments.
Extensive references to related material are also catcom. This problem can be addressed by approximating the twin vertical tails as a single equivalent vertical tail mounted to the fuselage. The values obtained can be used to calculate meaningful aspects of flight dynamics. Select a Web Site Choose a web site to get translated content where available and see local events and offers.
Tables which compare calculated results with test data provide indications of method accuracy. March Learn how and when to remove this template fatcom. Summary Table of Contents. A new methodology is then proposed which combines the datom 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. Retrieved from ” https: Drag due to a circular cavity in a plate with turbulent boundary layer at subsonic, transonic or supersonic speeds A This classification is summarized below: