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Expert designed and tested missles and spacecraft in many Hypersonic wind tunnels at elevated temperatures and pressures from Mach 3 simulation to Mach 8 simulation at NASA. The expertise included test procedures for starting such facilities and techniques to avoid damage to the test article. Spacecraft such as parts of the Space Shuttle were tested ; vehicles such as RV's were tested; and components such as tiles for the Space Shuttle were tested. Wind tunnels were designed for testing scramjets and other aerospace engines. The designs included the combustion chamber or plenum, the nozzle, the test chamber, and the diffuser. Some of the facilities are still in use today and are some of the largest wind tunnels in the world for Hypersonic testing and evaluation of missles and spacecraft and airbreathing engines.

Expert designed or improved combustion chambers for high temperature test facilities. These ranged from pressures of one atmosphere to 4000 psia, and temperatures from 1100 R to 5500R. The combustors were from 3 inches in diameter to over 3 feet in diameter. The problems solved were survival; heat transfer, stability, acoustics, ignition, and safety. Expert has 5 Patents in these areas. Some of the designs were unique and new such as the stabilized lifted flame and the combustor within a combustor. He designed a combustion chamber development facility that was used to test new designs and concepts. Two of the new designs were the stabilized lifted flame for methane and hydrogen, and the combustor within a combustor for good thermal profiles and broad coverage from 1100 R to 5500 R with one combustor.

He has developed effective acoustic damping techniques ( reduced noise in 8-FT HTT from 70 psi at 30 HZ to 0.5 psia at 360 Hz.- now the quietest combustor in the world for its size He has designed and tested and now in service, Super Ignitor for 8-FT HTT . Uses rich pilot flame ( REQ=3) to stabilize and ignite large jet of methane at near sonic conditions He has designed a development facility. In this facility, he designed a number of unique designs and tested :
i. The modified Lewis design for use as ignitor
ii. The mini-max SUE annular combustor
iii. A swirl stabilized combustor
iv. A ring type fuel injector
v. A modified ring type injector
vi. A lifted flame ring injector ( no cooling needed)
vii. A lifted flame paired airfoil injector able to operate at 5000 R and 2000 psia without cooling.
He lead the installion of 84 SUE combustors ( 52 foot diameter plenum ) in the 9 X6 Wind Tunnel . Temperature =2500 R and Poc=200 psia . Used to test Army and Air Force tactical missiles at q of up to 5000 psf . Flow rates of up to 5000 lb./s of which 60% went through combustors. The SAM-D ( now the Patriot was developed here ) ; the improved Hawk ;the use of fused silica as radomes ; radomes for rain and ice also developed here He was responsible ( with team) for the redesign of the Mixer for Aerojet for the Hypersonic Test facility