|
|
|
Foundation ::
Aerodynamics Applications ::
SCRAM
|
SCRAM
An Engineer's Tool for Prediction of Airframe Integrated Scramjet Performance
|
 |
Moderators:
Adopt This Application!
|
SOURCE CODE AVAILABLE
|
|
SCRAM determines the one-dimensional performance for an airframe
integrated supersonic combustion ramjet (scramjet). The supersonic
combustion ramjet cycle, which uses hydrogen for fuel and atmospheric air
for oxidation, is essential for the development of a propulsion system for
single-stage-to-orbit aerospace vehicles. These vehicles are intended
to be launched horizontally, as opposed to vertical launching for current
space vehicles. In addition, they must achieve hypersonic flight to Mach 25
prior to orbital insertion into low Earth orbit. The propulsion system of
these vehicles must be reusable, efficient, and cost effective.
The scramjet
cycle analysis code performs nose-to-tail, hydrogen fueled, Airframe
Integrated Scramjet (AIS) simulation in a real gas flow with equilibrium
thermodynamic properties. This allows ready generation of preliminary estimates
for SCRAM cycle performance. SCRAM is a reliable, efficient, and
speedy design tool that is useable on all standard computers down to IBM PCAT
compatible machines.
Developed in the Hypersonic Propulsion Branch at NASA Langley Research
Center for the Hypersonic Research Engine and Langley 3-Strut engine programs,
the current version of this code has been modified by the NASA Dryden
Flight Research Facility of the Ames Research Center for the purpose of
supporting the Langley Strutless Parametric engine and National AeroSpace
Plane (NASP) engine test programs.
The current version of SCRAM optimizes
the tradeoffs between the needs for computational speed, accuracy, and future
modifications. The program utilizes a five station geometry model,
with variable step size between each station, to analyze a vehicle noseto-tail
mass capture stream tube control-volume with real gas equilibrium
flow properties. SCRAM applies the laws of Conservation of Mass, Momentum,
and Energy across each step to calculate the changing flow parameters along
the control volume. The code incorporates an integral boundary layer code
based on the Spaulding-Chi Method to determine the friction coefficient,
and then utilizes a modified Reynolds Analogy to calculate heat transfer.
Although the code was primarily written for supersonic flows, it has been
modified to handle subsonic flows, along with the ability to handle DualMode
combustor operation.
SCRAM carries the NASA case number ARC-12338. It was originally released as part of the NASA COSMIC collection.
|
|
More software from National Technology Transfer Center
|
|
|
|
|
|
|
Open Channel Software runs entirely on Open Source Software. We return
value to the Software community in the form of
services and original software. Most of our
content is currently available as source code, with the
copyright owned by the original author, All
Rights Reserved. Everything else is Copyright
©2000, 2001, 2002, 2003, 2004, 2005, 2006, 2007, 2008 Open Channel Software.
View our privacy statement.
Contact webmaster at openchannelsoftware dot org with questions.
|
|
|
