AeroRocket Engineering
The sole source for AeroCFD
, FinSim, AeroSpike and HyperCFD

Providing Affordable Aerodynamics Software Since November 1, 1999





Latest Publications
Three-Stage Rocket Equation Analysis of the Saturn V Launch Vehicle
Excel Spreadsheet Multi-Stage Rocket Analysis, Technical Note 2023-1

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

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

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

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

"Demonstrating the Relationship Between
Quantum Mechanics and Relativity", viXra e-print archive (2019)

"Rocket Spin Stabilization Using Canted Fins", SpinSim (2002)
MathCAD document in this TN is copyright and requires permission to use

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.

SOFTWARE DISTRIBUTION HALTED: Since 1999 AeroRocket policy has been to avoid distribution of all dual-use supersonic rocket, hypersonic rocket and re-entry vehicle design software including AeroCFD, HyperCFD and FinSim to ALL countries under the control of communist, Marxist and totalitarian governments. In recent years we have come to realize that we cannot in good conscience continue to freely distribute our software in the USA because many requestors are guided by a pernicious form of Marxism called American Marxism. However, trusted friends will continue to receive our services.

"Freedom is a fragile thing and it's never more than one generation away from extinction. It is not ours by way of inheritance; it must be fought for and defended constantly by each generation..."
-- President Ronald Reagan

John Cipolla
Chief Aerodynamicist


Nozzle 10: Nozzle is a 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. The 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.

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.

FinSIM 10 and the new 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.

AeroCFD is a "true" three-dimensional axisymmetric and two-dimensional implicit finite volume CFD program that solves the inviscid Euler equations for subsonic, transonic and supersonic flow using automatic mesh generation and graphical results visualization. AeroCFD provides a maximum of 100 cells in the axial direction, 50 cells in the transverse direction and 10 cells in the circumferential (3-D) or thickness (2-D) direction. The latest version of AeroCFD has increased the number of discrete finite-volumes available for analysis from 18,000 cells to 50,000 cells. Due to its "true" 3-dimensional formulation, AeroCFD provides non-zero lift and non-zero pitching moment for axisymmetric shapes at angle of attack without requiring computational times exceeding one hour. Model geometry is specified by selecting from a library of standard shapes. Nose sections are defined using one of five basic shapes that include Conical, Ogive, Elliptical, Parabolic and Sears-Haack with power series coefficient. The user has the option for adding up to two constant diameter sections, one variable diameter transition section and one variable diameter boat tail section to complete the library of user-defined shapes. For added flexibility AeroCFD can import up to 1,000 X-R data points for generating axisymmetric and two-dimensional designs that require grid clustering in regions where shock waves dominate the flow. The RESULTS section clearly displays FX, FY, MZ, CX, CY, CM, CD, CL, base drag, surface friction drag and center of pressure location. Flow fields are displayed using fill-contour plots, line-contour plots and surface distribution plots for pressure coefficient, pressure ratio, temperature ratio, density ratio and Mach number. All output can be sent directly to a color printer.

AeroSpike performs an expansion-wave analysis from the throat of the thruster nozzle, where Mn = 1.0, to the thruster nozzle internal-exit as a series of simple wave expansions. Then, for the external ramp AeroSpike performs a series of Prandtl-Meyer expansions from the lip of the cowl, where R=Re, to the entire length of the external ramp of the aerospike nozzle. The ideal contour or shape of the external ramp of the aerospike nozzle is determined using isentropic supersonic flow theory. Then, depending on whether the flow is underexpanded or if the flow is overexpanded AeroSpike performs either a Prandtl-Meyer expansion analysis or an oblique shock wave analysis to determine the angle of the outer flow boundary from the lip of the cowl. As a by product of the oblique shock wave analysis AeroSpike determines the shock wave angle for overexpanded flow and plots both the outer boundary contour and the initial shock wave from the lip of the cowl.

StarTravel performs two-body astrodynamics analyses of spacecraft and satellites knowing burnout velocity and flight-path angle at burnout. For this purpose StarTravel uses two-body astrodynamics theory for determining sub-orbital, orbital and interplanetary motion around the Earth and Sun. In addition, StarTravel performs general heliocentric and Hohmann Transfer orbital analyses for determining minimum velocity and flight time required for travel from Earth to other planets in the solar system. StarTravel also has a Solar System Calculator for animating orbital motion of the planets around the Sun. Finally, StarTravel uses the Special Theory of Relativity to determine elapsed time on Earth and aboard our starship when speeds approach the speed of light and determines the relativistic Doppler frequency shift of star light observed by our starship in the form of a color contour plot of the firmament. New in the latest version is the ability to determine the ballistic trajectory of  rockets and missiles launched vertically, horizontally and everything in between.

Additional Links
Author's viXra
e-print archive
Warp Drive Research Contact AeroRocket


AeroCFD is a registered trademark of John Cipolla/AeroRocket
Copyright 1999-2024 John Cipolla/AeroRocket & WarpMetrics
Site updated 07/18/2023