Latest Publications
“Potential Vortex Transient Analysis and Experiment”, viXra e-print archive, (2014)
"Hydrodynamic Analogue for Curved Space-Time and General Relativity", viXra e-print archive, (2014)
"Computational and Experimental Interferometric Analysis of a Cone-Cylinder-Flare Body", AIAA, (1989)

Experimental Rocket Launches
Sprint Experimental Rocket
Sprint Model Rocket

Nozzle 3.7 Example: External shock pattern for an overexpanded SSME rocket nozzle. Nozzle 3.7 is a one-dimensional isentropic with cross-sectional area variation, compressible flow computer program for the analysis of converging-diverging nozzles. 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 3.7 applying the concept of a normal shock diffuser. Finally, use AeroRocketCAD to generate Nozzle 3.7 and AeroCFD shapes from AutoCAD DXF geometry. More ...

AeroCFD 5.2 Example: The Masten Space Systems XA-1.0 vertical takeoff rocket has been modeled using AeroCFD 5.2. AeroCFD is a "true" three-dimensional axisymmetric and two-dimensional 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 finite-volumes available for analysis from 18,000 cells to 50,000 cells without increasing run time. Due to its "true" 3-dimensional formulation, AeroCFD provides non-zero lift and non-zero pitching moment for axisymmetric shapes at angle of attack. 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. 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. See how to easily perform high power rocket CFD's and generate multiple fin sets using AeroCFD. See the new AeroCFD demo which illustrates how simple it is to plot flow fields, determine Cd and Xcp using AeroCFD.

SUPERSONIC BLOW-DOWN WIND TUNNEL (1" DIAMETER)
A new supersonic blow-down wind tunnel is available for testing aerodynamic shapes. The new 1" inside-diameter supersonic blow-down wind tunnel, having a test section blockage factor less than 3%, now joins the successful 1/2" supersonic wind tunnel. The AeroRocket 1" diameter supersonic blow-down wind tunnel performs drag measurements up to Mach 3. In addition, AeroRocket's expertise in the fabrication of miniature wind tunnel models makes possible the measurement of supersonic drag coefficient for designs ranging from simple high power rockets to the very complex HTV-3X and X-30 NASP. Mach number verses time is measured during the blow-down process using a pitot-static pressure probe for measuring total pressure (Po) and static pressure (Ps) of a compressible fluid in this case air. Click here to view a QuickTime movie of a 2.5 second segment of a typical blow-down wind tunnel test using the 1" diameter supersonic wind tunnel where nearly constant Mach 1.6 flow is maintained for approximately 2.5 seconds, an eternity compared to typical shock tube performance.

StarShip VASIMR Analysis: 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 for determining sub-orbital, orbital and interplanetary motion around the Earth and Sun. In addition, StarTravel performs general heliocentric and Hohmann Transfer orbital analyses. New in the latest version of StarTravel is the ability to determine the ballistic trajectory of  rockets and missiles launched vertically, horizontally and everything in between. Also, perform a Variable Specific Impulse Magnetoplasma Rocket (VASIMR) analysis or a standard constant specific impulse analysis (nuclear propulsion) by specifying starting exhaust velocity and ending exhaust velocity or constant exhaust velocity for heliocentric flight to planets and stars.
 

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Site updated 01/21/2015