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Providing Affordable Aerodynamics
Software Since November 1, 1999
John Cipolla's IQ
WHY Consider John Cipolla and AeroRocket
exceptional creativity in Computational Fluid Dynamics (CFD),
Finite Element Analysis (FEA) and
composite material analysis for aerospace applications.
Proven computer programming ability using Microsoft Visual Basic,
FORTRAN and C++. Not just theoretical but "real world"
experience in subsonic, supersonic and hypersonic wind tunnel
testing and related CFD analysis and experiments.
experienced in the
industrial use of sophisticated numerical analysis techniques to
enhance productivity and reduce final product cost.
AeroRocket and WarpMetrics
Aerodynamics, structures, materials, applied
mechanics and space propulsion.
Also, Computational Fluid Dynamics (CFD), wind tunnel testing,
Finite Element Analysis (FEA), General Relativity, quantum
mechanics, particle physics and composite materials analysis &
was attacked on the Withlacoochee State
Trail in Citrus Springs, Florida
Please see GoPro
video derived images and video of the violent attack on John Cipolla
while bicycle riding the Withlacoochee State Trail in Citrus Springs,
Florida. Two bicycle riders jealous of John Cipolla's bicycling ability and
speed, destroyed John Cipolla's $6,000 bicycle and helmet today
valued at over $12,000. The attackers got away with only paying John
Cipolla $1,240 for their vandalism.
Wind Tunnel Testing and Aerodynamics
provides wind tunnel testing for the determination of LIFT (CL) and
DRAG (CD) coefficients for almost any aerodynamic shape using its
own subsonic wind tunnel. The wind tunnel at AeroRocket's
disposal was developed in-house to provide a wide range of lift,
drag, velocity and pressure profile measurements for any shape
imaginable. The test section is 7 inches wide x 10 inches high x 16
inches long. Maximum test section velocity is 80 ft/sec without a
test item installed. The AeroRocket wind tunnel is ideal for
measuring the subsonic drag of unusual designs and shapes not
treated by AeroDRAG™ or other rocket analysis computer
programs until the development of
The AeroRocket subsonic wind tunnel
is ideal for measuring drag and lift using the in-house built
two-component force balance system.
subsonic wind tunnel is routinely used for defining the aerodynamic
properties of new designs and for validating the design of vehicles
like the Schafer Corporation ultra-high altitude V-Ship.
AeroRocket's new supersonic
blow-down wind tunnel having an inside-diameter of 1.03
inches and Mach 3 capability is operational and being used to design
HFV-3X spacecraft for transonic and
supersonic flow. In addition,
unique expertise in the fabrication of miniature supersonic wind
tunnel models allows testing realistic shapes for accurate flow
field and CD measurements for a wide variety of R&D applications,
including the HFV-3X and other supersonic designs.
Primary Aerospace design engineer for the 800
Facility, also known as the ARF, located at Eglin AFB. Florida.
As primary mechanical designer of the ARF,
responsible for design, fabrication and installation for dozens of major
components. Designed complex free-flight
used to measure subsonic and supersonic projectile
position, velocity, stability derivatives (CNa,
and aerodynamic coefficients (Xcp, Cd, CL). Free-flight tests
conducted in the ARF are used to validate innovative high speed
projectile designs and related CFD results.
The ARF engineering design effort continues to have a direct
positive impact on many Army, USAF and NASA projects. Successfully utilized the ARF
test facility to publish papers concerning the
Interferometric prediction and validation of air
density flow field distribution of a cone-cylinder-flare
projectile in free-flight and the CFD analysis of missile
configurations in supersonic flight. Many USAF personnel use the ARF to publish
research papers sponsored by the AIAA and to support their Phd
Dynamics (CFD) and Propulsion
EXPERIENCE: Project manager and principal developer of new
Computational Fluid Dynamics and high power rocket analysis computer software.
for the compressible fluid flow analysis of model and high power rockets. AeroCFD®
is a three-dimensional axisymmetric and two-dimensional
finite-volume numerical analysis computer program that solves the
steady and unsteady inviscid Euler equations for subsonic,
transonic, and supersonic flow. AeroCFD®
generates flow fields by applying automatic numerical grid
generation and mesh distribution around a library of standard
aerodynamic shapes. Complex CFD solutions are achieved in minutes
rather than hours greatly increasing aerodynamic design
PROPULSION EXPERIENCE: Developed
an affordable program for the
generation of thrust-time predictions for new solid fuel
rocket motors and curve-fit analyses of new rocket propellants.
Developed several other software applications for the analysis of
model rocket, high power rocket and professional (full-scale) rocket
aerodynamics. Specifically, developed
for the performance analysis of standard nozzles and the next
generation aerospike rocket motors. For
the Strategic Defense Initiative (SDI) developed the first magnetic
field finite element analysis (FEA) computer program for determining
the internal and external forces experienced by electro-magnetically
(EM) propelled hypervelocity projectiles. Later, other companies
developed similar magnetic field finite element analysis capability,
but John Cipolla's magnetic field finite element analysis was the
first available at Eglin AFB for modeling electro-magnetically
launched hypervelocity projectiles.
FLUENT and GAMBIT used to solve complex
3-dimensional turbulent fluid flows in process control valves.
Using Fluent CFD
John Cipolla invented
an innovative valve trim or insert capable of controlling
cavitation and reducing valve induced noise level by several dB.
This new valve insert design was made possible because John
Cipolla was able to draw upon previous aerospace experience
where similar methods and devices are used to reduce sound
pressure level in aircraft open bomb bays when operating in the
transonic, supersonic and hypersonic environment.
Related Aerodynamics and CFD Experience
--Software development for new grid generation and CFD flow
--Project manager for a USAF project to analyze separation of
bodies in hypersonic flow.
--Developed methods to model high-temperature equilibrium
flows for hypersonic vehicles.
--Program management of new CFD program code development at
--Aeroelastic and structural analyses of F-15, F-16, A-10 and
B-52 aircraft/weapon compatibility.
--Participated in the development of electro-magnetically (EM)
launched projectiles for SDI.
--Aerodynamics and structural analyses for the AMRAAM
John Cipolla's "firsts" in the areas of
aerodynamics and CFD
--Developed 3-D multi-block missile CFD model using the CRAY-2
--Developed a fully viscous cavity flow CFD simulation of a
fighter aircraft open bomb bay.
--Predicted total missile drag and free flight static stability
derivatives using EAGLE CFD code.
the Eagle CFD code, theoretical basis
of the AFSEO Beggar CFD code, used by the United States Air Force SEEK
EAGLE Office to conduct time accurate store separation analyses.
Experienced in the industrial
use of sophisticated Finite Element Analysis (FEA) methods to
enhance productivity and reduce final product cost. This
valuable experience has been in the areas of static and dynamic
COSMOS/M finite element analysis software.
Developed and coded several FEA computer programs for USAF
in-house use in the areas of structural analysis, fluid dynamics
and electromagnetic and magnetic fields. Experience using
AutoCAD and ProEngineer computer aided design software for
sophisticated design efforts. Finally, solid experience using
PDEase2D for the
analysis of field problems in structural mechanics and fluid
STRUCTURAL ANALYSIS: Performed complex structural and
aeroelastic analyses of USAF aircraft/store compatibility for
flight test certification. Planed and performed engineering
studies for the design and flight test of weapons being procured
by the Air Force Materiel Command. Incorporated several new
armament and launcher combinations into the F-15 and F-16
aircraft flutter simulations. This work required in-depth
knowledge of MSC/NASTRAN to perform aeroelastic and flutter
simulations of the F-111, F-15 and F-16 aircraft. During Desert
Storm, certified the GBU-28 laser guided super bomb called the
"Bunker Buster" for carriage aboard the F-111 and F-15 aircraft.
Finally, for the Strategic Defense Initiative (SDI) analyzed the
dynamic response of EM launched kinetic kill vehicles (KKV)
accelerated to 100,000 G's. MSC/NASTRAN and classical stress
analyses used to determine Von Mises stress levels in the
projectile airframe during electro-magnetic rail gun launch.
COMPOSITE MATERIALS: While working for the USAF developed the
algorithm and matrix equation solution for the in-house paper,
Analysis of a Forward-Swept Wing with Stiffness Cross-Coupling".
This analysis made possible the rapid parametric design of
composite material forward-swept wings. Also,
experienced in the
theoretical analysis of aerospace structures that use composite
materials for stiffness cross-coupling like forward-swept wings,
composite shells and single-piece filament-wound graphite epoxy
casings for solid fuel rocket motors. Developed methods to model
carbon-carbon composite material nose cone ablation for EM
launched SDI projectiles. Also, performed a finite element
structural analysis for an early GBU-15 composite-wing transonic
PIEZOELECTRIC MATERIALS (ACOUSTICS): While working for Raytheon
developed a FORTRAN-77 based computer program for the design of
underwater sonar transducers. PESAP (Piezo-Electric
Structural Analysis Program) incorporated
an electrodynamic piezoelectric finite element in addition to
the standard constant strain finite element. PESAP successfully
predicted resonance frequency, modal patterns, input electrical
admittance verses frequency and modal displacements for several
U.S. Navy underwater sonar transducers. PESAP more accurately
modeled the interaction between complex modes of vibration and
the acoustic environment than other methods that were available.
Warp Drive Basic
Cipolla is performing innovative research in the area of
technology for faster than light star travel.
The image to the left shows a spacecraft being propelled while
enclosed within an artificially generated warp bubble.
A warp bubble based on the
concepts of General Relativity uses opposing regions of
expanding and contracting spacetime for propelling a
starship at velocities exceeding the speed of light. This is a
work in progress based on a new method for warping spacetime to
generate warp bubble disturbances without the need for exotic
matter or negative energy.
Self-employed aerospace engineer and
computer programmer. Deeply involved in desktop publishing for
the Internet and the application of computer programs for
producing high impact graphics and animations for e-commerce web
pages. Extensive experience using UNIX, Microsoft Windows and
Macintosh operating systems.
Related Computer Programming Experience
--CFD code development using FORTRAN-77.
AeroDRAG™ to compute rocket drag to Mach 20.
--Developed CFD applications for high speed rockets:
--Experienced in industrial R&D and web page computer
--Create, operate and manage the AeroRocket e-Commerce web
--Internet publishing using Microsoft FrontPage, Adobe
Photoshop, Adobe Illustrator.
--Automated several ASME Code pressure vessel design
computer programs using VB-6.
--Mathematical capability enhanced by
Maple V, MathCAD, Theorist and Excel.
Patents and Trademarks
John Cipolla registered the
trademark (number 2992220) with the United Stares
Patent and Trademark Office on September 6, 2005 for the
following description of Goods and Services: COMPUTER
SOFTWARE THAT USES THE METHODS OF COMPUTATIONAL FLUID DYNAMICS (CFD)
FOR THE PREDICTION OF MODEL ROCKET DRAG, LIFT AND MOMENT
COEFFICIENTS; THIS SOFTWARE IS USED FOR DESIGNING MORE
AERODYNAMICALLY EFFICIENT ROCKETS.
by John Cipolla
"Proving Shock Thickness
Decreases for Increasing Mach Number",
Thickness Analysis, (2020)
"Demonstrating the Relationship
Between Quantum Mechanics and Relativity",
"External-Jet (Fluid) Propulsion Analogy
for Photonic (Laser) Propulsion",
archive, (2016, 2017)
"Does Time Exist",
Transient Analysis and Experiment”, viXra
e-print archive, (2014)
"Hydrodynamic Analogue for Curved Space-Time and General
e-print archive, (2014)
"V-Ship Wind Tunnel Drag and
Lift Estimation Compared to Cylinder Cross-Flow", Schafer Corp.,
"Computational and Experimental Interferometric
Analysis of a Cone-Cylinder-Flare Body",
"Aerodynamic Test and Analysis of a Slender Generic
"Aeroelastic Analysis of a Forward-Swept Wing with
Stiffness Cross-Coupling", AFAL TECH NOTE, (1989)
"Program EAGLE Users Manual", AFATL-TR-88-117, Vol. I, (1988)
"Program EAGLE Numerical Grid Generation System User's
Manual", AFATL-TR-87-15, Vol. II, (1988)
"Radiating Head Flexure and Its Effect on Transducer
Performance", JASA, Raytheon S.S.D., (1981)
"A Unique Alignment System", Aeroballistic Research
design summary, AFAL, (1975)*
Note the Following
Except as noted John Cipolla is primary investigator or sole author for
the technical papers presented above.
(*) John Cipolla is the main author for these technical papers.
JOHN CIPOLLA'S AUTHORSHIP
DISPUTE WITH THE AIAA and AFAL
and AFAL used John Cipolla's research without permission
and did not recognize his work for
--- SCREEN SHOTS
Report and Final AFAL Briefing, November 10, 1989
"Computational and Experimental Interferometric
Analysis of a Cone-Cylinder-Flare Body"
Final Report: Click to download
ARF Experimental Interferogram
CFD Four Block Mesh
CFD Theoretical Interferogram
CFD Density Contours
DISPUTE: In an authorship dispute submitted to the AIAA ethics committee in January 2015, the
American Institute of Aeronautics and Astronautics (AIAA) was requested to acknowledge John Cipolla's contribution as coauthor for the
AFAL portion of the AIAA paper,
AIAA-1990-0621. In their finding the AIAA admitted that John Cipolla’s research represents "similar work" as performed in AIAA-1990-0621, was “unique within AFAL”, and published before the January 8-11, 1990 publication date of AIAA-1990-0621. In fact, John Cipolla's
final report was submitted on November 10, 1989 and included a briefing and handouts to all AFAL personnel including at least one author of AIAA-1990-0621.
However, even after acknowledging as valid a signed letter from a high ranking AFAL, CFD Section supervisor who stated
the following in a signed letter, the AIAA continues to deny John Cipolla’s authorship
of this important technical paper.
"This proved to be a new and innovative method for CFD code validation
methods and was reported by John et al in an AIAA conference paper"
The AIAA also ignored signed letters from two other supervisors stating John Cipolla made significant contribution
to this work. In
addition, we believe the wording and concepts expressed by the following
copyright 1989 material from John Cipolla’s final report was used
without permission by the AIAA and AFAL, “The ability to measure
these effects and to calibrate and validate
existing computational methods is essential to designing efficient
high-speed vehicles and to minimize heating and ablation effects. A
nonintrusive technique to measure these effects and to produce a
database for comparison with CFD results is essential to remove the
uncertainty of physical measurement systems”. The authors used
the keyword calibrate three times and in one instance used
the keyword calibrated in quotes without reference to its origin in relation to CFD/holographic technology. Conflating the
terms validate and calibrate is not common practice in the aerospace
industry and are not common themes in the industry when validation
occurs in CFD code development and not calibration. John Cipolla's concept of
calibrating CFD codes revealed during his briefings and final report
appear to have been adopted without recognition in AIAA-1990-0621.
In addition, even AIAA-1985-1564, the basis for AIAA-1990-0621 and
the main reference for the work never once used the word “calibrate”
at any point in the paper.
The referenced AIAA conference paper was located using AIAA’s new
ARC technical document retrieval system and was presented at the 28th Aerospace Sciences Meeting, held January 8-11, 1990 in Reno Nevada. In our opinion this type of behavior is known as “denial of authorship” and is an AIAA publication ethical violation.
email AeroRocket to see the complete summary
of AeroRocket's year long AIAA ethics investigation pertaining to the authorship
dispute for AIAA-1990-0621.
1) American Institute of Aeronautics and Astronautics (AIAA)
Armament Laboratory, (AFAL now a unit of AFRL) Eglin AFB
3) Aerospace Research Central (ARC),
AIAA's new technical document retrieval system
Visual Basic 6, FORTRAN 77/90, C++, UNIX, FLUENT
& GAMBIT, MSC/NASTRAN, COSMOS/M, Excel, MathCAD, Photoshop,
FrontPage, PDEase2D for differential equations and various CAD
Element Analysis (FEA)
Computational Fluid Dynamics (CFD)
Numerical Grid Generation for FEA & CFD
Composite Materials Analysis
Rocket and Space Propulsion
AIAA - American
Institute of Aeronautics and Astronautics, Senior
Member, 1981 to 2015
Resigned AIAA membership to protest denial of authorship
and use of my research without permission or
Pi-Tau-Sigma - Mechanical
Engineering Scholastic Honor Society
is a registered trademark of John
Copyright © 1999-2020 John Cipolla/AeroRocket