Sign in to download full-size image Fig. 15. SR-72 Turbine-based combined cycle propulsion (Source: [69]). 4.2.2 Additional methods There are some additional methods to produce extra propulsive force or reduce drag on an aircraft. Some of these methods are still at an early stage of deve...
Sign in to download full-size image FIGURE 4.5.7. A continuous operating, open-circuit, free jet supersonic wind tunnel. Figure 4.5.8 provides a schematic view of the CNRS-SR3 (located in Meudon, France) continuous open-circuit facility, which simulates rarefied flow conditions. In such a ...
Material requirements are further exacerbated due to the dissociation of O2and N2into free radicals at gas-phase temperatures above 3000 °C (typically at speeds greater than Mach 8). These conditions lead to highly reactive surface chemical interactions, causing materials degradation, microstructural ev...
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Full size image Among the UHTCs, ZrB2-SiC and HfB2-SiC have received the most attention because they uniquely combine high thermal conductivity, specific strength (σ > 460 MPa at T = 2500 °C,ρ = 5.5 g/cm3 83), and superior oxidation resistance ~1650 °C78,80,84. ...
Full size table An explosive pressure rises over the leading edge in hypersonic flow and encloses by a shock envelope with an inclining Mach angle with respect to the freestream. The blast wave theory also recognizes that the bow shock shape is relatively insensitive with respect to the wave ...
Download free sample pagesMore information In addition to developing precooler technology, Reaction Engines is developing and testing novel high-Mach intake designs and technology for hypersonics capabilities. Hardware is currently being manufactured and assembled for a full-scale ground-based...
Sign in to download full-size image FIGURE 4. Characterization of flow fields based on the Mach number range. [From Anderson, J. D., Jr. (2001). “Fundamentals of Aerodynamics” 3rd ed., McGraw-Hill, New York.] 2. Transonic flow (mixed regions where M < 1 and M < 1). As stated...
Sign in to download full-size image Figure 1.9. Temperature after a normal shock wave as a function of free-stream velocity at a standard altitude of 52 km.From Viviani, A., & Pezzella, G. (2015). Aerodynamic and aerothermodynamic analysis of space mission vehicles. In Springer aerospac...
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