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AeroCFD For Mac OS X
Instruction Manual
Drag Coefficient (Cd) To Mach 10
and
Single Stage to Orbit Flight Analysis
REASONS FOR DISCONTINUING
AEROCFD FOR MACINTOSH
1. Macintosh users lack of interest (20%)
2. Serious errors and limitations in Xcode (60%)
3. Technical support not available from Apple (20%)
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MAIN
PAGE |
PRODUCTS | CONSULTING | MISSION | RESUME |
Copyright © 1999-2011 John Cipolla/AeroRocket. All rights
reserved |
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AeroCFD
for Mac OS X
(version 10.6.0 or later) is a rocket analysis computer program that uses
Apple's Xcode IDE and C++ to compute drag coefficient (Cd)
up to Mach 10 and computes maximum altitude and maximum
velocity for single stage and suborbital rockets for the low price of
only $20.
Summary of Features
1) Tool tip
description for each input variable.
2) Plot drag coefficient (Cd) verses Mach number (Mn) to
Mach 10.
3) Display Cd at a specified Mn.
4) Display drag components at a specified Mn.
5) In Flight mode display maximum velocity (dV),
maximum altitude (Hmax), propellant flow rate (Mp) and
exhaust velocity (c) knowing rocket thrust, specific
impulse (Isp), initial mass, final mass, average rocket
Cd and maximum airframe diameter.
Macintosh System Requirements
Architectures: Standard (32/64-bit Intel)
Base SDK: Mac OS X 10.6
Valid Architectures: i386 ppc ppc64 ppc7400 ppc970
x86_64
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Figure-1, Model rocket Cd verses Mn analysis, 67% of actual
size
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To
determine drag coefficient (Cd) verses Mach number (Mn)
for single stage suborbital rockets simply insert a
value for Mn greater than zero (> 0) in the first text
box on the main screen and press return. Then, insert
the required design information specified in the dark
gray area and the remaining data into the text boxes
provided. After entering data for each text box press
tab to advance to the next text box until all the
rocket design information is specified. When data in the
final text box is specified press return to
display a plot of Cd verses Mn and drag (Cd) contribution
for each component. The results illustrated in Figure-1
display Cd verses Mn for a typical model rocket |
Figure-2, SS1 flight analysis, 67% of actual size
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To
determine maximum velocity (dV) and maximum altitude (Hmax) for
single stage suborbital rockets simply insert zero (0)
in the first text box on the main screen and press
return. Then, insert Rocket Thrust (nt), Isp (sec),
Initial Mass (kg), Final Mass (kg), Average Rocket Cd,
and Maximum Diameter (cm) in the text boxes
corresponding to the dark gray area. The text box
entries outside the dark gray area may be ignored for
the Fiight Analysis. After entering data into
each text box press tab to advance to the next
text box until all flight information is
specified. When data corresponding to the final text box
in the dark gray area is entered press return to
display Maximum velocity (m/sec), Maximum
altitude (km), Propellant mass flow rate (kg/sec) and
Exhaust velocity (m/sec). The results illustrated in
Figure-2 display flight information for
SpaceShipOne. |
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Figure-3, V-2 rocket Cd verses Mach number analysis, 67% of
actual size
|
To
determine drag coefficient (Cd) verses Mach number (Mn)
for single stage suborbital rockets simply insert a
value for Mn greater than zero (> 0) in the first text
box on the main screen and press return. Then, insert
the required design information specified in the dark
gray area and the remaining data into the text boxes
provided. After entering data for each text box press
tab to advance to the next text box until all the
rocket design information is specified. When data in the
final text box is specified press return to
display a plot of Cd verses Mn and the drag (Cd) contribution
for each component. The results illustrated in Figure-3
display Cd verses Mn for the full scale hypersonic
V-2 rocket. |
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Back to TOP
|
MAIN
PAGE |
PRODUCTS | CONSULTING | MISSION | RESUME |
Copyright © 1999-2011 John Cipolla/AeroRocket. All rights
reserved |