AeroRocket Engineering

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Providing Affordable Aerodynamics Software Since November 1, 1999

 

 

 


 

Latest Publications
FinSim Rocket Equation Burnout Velocity Accuracy Compared to
Finite Difference and TR-10 Prediction,
viXra e-print archive (2022)

Ring Fin Rocket Center of Pressure, Drag and Lift Slope Coefficients
Measured Using the AeroRocket Wind Tunnel, Technical Note 2022-2 (2022)


Spool Rocket Center of Pressure and Drag Coefficient Measured
Using the AeroRocket Wind Tunnel, Technical Note 2022-1 (2022)

Warp Drive Propulsion Using Magnetic Fields to
Distort Space-Time OR
First Successful Warp Drive Flight (2021)

POF 291 Flutter Velocity Error Produces Negative Margins of
Safety Compared to NACA TN 4197, Technical Note 2021-2 (2021)

FinSim 10 Torsional Stiffness of Rocket Fins
Thickness-Tapered From Root to Tip, Technical Note 2021-1
(2021)

"Proving Shock Thickness Decreases for
Increasing Mach Number", Shock Wave Thickness Analysis (2020)


"Demonstrating the Relationship Between
Quantum Mechanics and Relativity", Theory of Everything (2019)

Experimental Rocket Launches
Micro-vehicles Launched on Jets of High Velocity Water
HTV-3X Space Plane Development

Sprint Experimental Rocket

Sprint Model Rocket

AeroRocket specializes in subsonic, supersonic and hypersonic aerodynamics, Computational Fluid Dynamics (CFD), warp drive physics and aerospace related software development for rockets, airplanes and gliders. Other services include wind tunnel testing using the AeroRocket designed and fabricated subsonic wind tunnel and supersonic blow-down wind tunnels.

AeroCFD® is a registered trademark of John Cipolla and is classified as an axisymmetric 3-D and planar 2-D Computational Fluid Dynamics (CFD) computer program. However, AeroCFD solutions are not limited to bodies of revolution even though AeroCFD's bodies of revolution can be very complex.

John Cipolla
Chief Aerodynamicist,
AeroRocket and WarpMetrics


 

Nozzle 10: One-dimensional and two-dimensional, compressible flow computer program for the analysis of converging-diverging nozzles, including ramjet and scramjet engines. Nozzle models inviscid, adiabatic and hence isentropic flow of a calorically perfect gas through variable-area ducts. Nozzle internal flow may be entirely subsonic, entirely supersonic or a combination of subsonic and supersonic including shock waves in the diverging part of the nozzle. Shock waves are clearly identified as vertical red lines on all plots. Nozzle 3.7™ Copyright © John CipollaThe cross-sectional shape in the axial direction of the nozzle is specified by selecting from five standard nozzle types or by defining nozzle geometry using the Free-Form nozzle geometry method. Nozzle plots color contours of pressure ratio, temperature ratio, density ratio, and Mach number and has a slider bar that displays real-time values of all nozzle flow properties. New in this version is the ability to determine shock-angle, jet-angle (plume-angle) and Mach number for axisymmetric and two-dimensional nozzles in the region near the lip for underexpanded and overexpanded flow. The converging-diverging nozzle featured in the new AeroRocket supersonic blow-down wind tunnel was designed using Nozzle applying the concept of a normal shock diffuser. More ...

HyperCFD 10
: Supersonic and hypersonic re-entry vehicle and rocket analysis computer program based on advanced principals of 3-D Gasdynamics. HyperCFD, determines drag coefficient (Cd), center of pressure (Xcp), CN-alpha and Cm-alpha of supersonic and hypersonic rockets and re-entry vehicles. In addition, on a separate screen HyperCFD displays and plots CN-Body, CN-Fins, CN-Total and Cm-Total as a function of angle of attack (AOA) using up/down controls. HyperCFD uses empirical aerodynamic corrections to the modified Newtonian surface inclination method that allows excellent results from Mach 1.05 to Mach 20. Includes a wide variety of nose cone shapes and fin cross-sections. Nose cone shapes include, conical, elliptical, parabolic, power series Sears-Haack, tangent ogive and spherical segment. Fin cross-sections include single wedge, symmetrical double wedge, arbitrary double wedge, biconvex section, streamline section, round-nose section, and elliptical section fin shapes. HyperCFD is useful to determine supersonic and hypersonic rocket drag and center of pressure location for medium and large scale professional sounding rockets. Finally, HyperCFD 10.xx models hypersonic glide vehicle (HGV) aerodynamics. More ...

FinSim 10, Flutter Velocity Tool: Quickly and easily predict fin flutter velocity, UF and fin divergence velocity, UD for any rocket while specifying fins in the Fin Geometry screen by simply using a slider bar. Predict flutter velocity from sea level all the way to maximum altitude that was defined on the main AeroFinSim analysis screen. Get instant flutter velocity feedback while specifying fin geometry and get an idea of fin shock angle and fin Surface Mach number that a fin will experience during supersonic flight. Flutter velocity accuracy is enhanced by using the NASA web site atmospheric model that predicts free stream pressure (P) temperature (T), density (r)and speed of sound as a function of altitude from sea level while flying through the Troposphere (h < 36,152 feet), Lower Stratosphere (36,152 feet < h < 82,345 feet) and finally the Upper Stratosphere (h > 82,345 feet). The atmospheric model used in FinSim is not limited to only the Troposphere or 36,152 feet. More ...
 

Special Links
    Magnetic Levitation Warp drive analysis
Magnetic Levitation and
 Warp Drive propulsion
AeroRocket References
Reference Books
Enclosed flow lift analysis
Ducted Wing and VASIMR
Plasma Rocket Propulsion
 
X-30 NASP AeroWindTunnel analysis
X-30 NASP
SS1 wind tunnel testing
SpaceShipOne
HTV-3X wind tunnel tests
HTV-3X

Some Validation Analyses

Shock Thickness | AeroSpike Validation | Nozzle Validation (1) | Nozzle Validation (2)
AeroCFD V-2 Analysis | AeroCFD Cone-Cylinder Analysis | SS1 Spaceplane Analysis | Rocket Center of Pressure
Companies that use AeroRocket Software

Additional Links
Contact John Cipolla
Contact
Chief Aerodynamacist
Author's viXra
e-print archive
UFO Research
and other stuff

Software Comments

 

Proof Biden Is Compromised By
Communist China, Russia and Iran
News Source: Fox News, August 21, 2022
FAMILY ACCEPTED $31M FROM DEALS IN CHINA
FAILED TO DEMAND COVID ORIGINS INVESTIGATION
CONSIDERING LIFTING TARIFFS ON CHINESE IMPORTS
SENDING OIL FROM AMERICA'S STRATEGIC RESERVE TO CHINA
CANCELED THE CHINA INITIATIVE THAT STOPPED CHINA SPYING
PUSHING ELECTRIC VEHICLE, SOLAR PANELS AND BATTERIES FROM CHINA
JOE BIDEN FAILED TO CONFRONT COMMUNIST CHINA FOR
USING FENTANYL AS A WEAPON OF
MASS DESTRUCTION
Democrat-Marxist voters are directly responsible for these failures and the resulting loss of American lives

Impeach Biden for allowing the invasion of millions of military aged men across USA's southern border including the smuggling of fentanyl that kills over 110,000 young Americans ages 18 to 45 every year, unilaterally destroying America's energy independence, emboldening the Russians and Chinese by showing weakness in Afghanistan, personally compromised by corrupt family foreign-influence deals with the Chinese Communist Party and selling strategic oil to China. Finally, Biden must be impeached because of the weaponization of the FBI against peaceful conservatives. In addition, several FBI agents are paying the price for exposing unjust ‘persecution’ of conservatives intended to advance the socialist-Marxist agenda of the FBI, DOJ and President Joe Biden.

IMPORTANT NEWS ALERTS

 
Metaphor for how "Let's Go Brandon" is damaging the United States of America

We Support the People of Ukraine
in the Battle to Defeat Russia


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AeroCFD® is a registered trademark of John Cipolla/AeroRocket
Copyright © 1999-2022 John Cipolla/AeroRocket & WarpMetrics
Site updated 09/22/2022