A review was made of the basic shock tube along with the various modifications required to produce hypersonic flow of short duration. Modifications to the driver system include multiple diaphragms, area discontinuities at the diaphragm station and combustion drivers. The influence of real gas effects, including shock wave attenuation, was noted for both the production of strong shocks M sub s 3 and the creation of hypersonic flow in an expansion nozzle. Nonreflected, reflected and tailored-interface type shock tunnels are discussed along with their starting problems, real gas effects and Reynolds number and stagnation temperature simulation. Detailed calculations were omitted for simplicity but many figures were presented which illustrate the operation of the various shock tube configurations. Further details may be obtained from the references given. The advantages and disadvantages of the various methods of producing hypersonic flow are summarized on the following pages.