In this paper, aerodynamic testing carried out with the JF12 hypervelocity shock tunnel is reported, and three experiments are discussed. The first experiment is aerodynamic heat test in hypersonic boundary layer, and a new thermal sensor for heat flux measurement at the extreme high-temperature condition is described, and the hypersonic boundary physics is explored. The second one is the aerodynamic force testing, and a new concept is proposed for optimizing the force and moment measurement system in shock tunnels. With this technology, the real gas effect is investigated, and its dominating mechanism is considered to be the gas molecular vibration. The last is the scramjet test from which two engine operation models are observed, that is, the continuous and pulsed combustion. Because most of the scramjet tests were conducted in combustion-based test facilities, the experimental data at the duplicated hypersonic flight condition would be of fundamental importance for exploring coupling of combustion, supersonic flow, and shock dynamics.