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The current work is undertaken to examine the capability of a recently developed ICFM (internal conical flow M) basic flowfield Musa et al., AIAA J. 61, 1–16 (2023) to design hypersonic internal waverider intakes. The osculating axisymmetric flows concept is employed alongside the streamline-tracing method to design three internal waverider intakes with different contraction ratios, i.e., 6.0, 9.0, and 25. The three intakes have similar capture and throat shapes and entrance areas. Then, the starting characteristics of designed intakes were investigated at different design and off-design conditions. The selected design condition is the flight at Mach 6.0 and 28 km altitude. Viscous computations have been performed at Mach 6.0, 5.0, 4.0, 3.9, 3.8, 3.5, and 3.0 for the intake with a contraction ratio of 6.0, and at Mach 6.0, 5.0, 4.7, and 4.0 for the intake with contraction ratio of 9.0. The intake with a contraction ratio of 25 is simulated at Mach 6.0 and 5.0. Successful intake starting has been achieved up to Mach 3.8 for the first intake and up to Mach 4.7 for the second intake. The intake with a contraction ratio of 25 attained an unstart state in the design condition due to a very high contraction ratio. Thus, the starting limit of internal waverider intakes designed using ICFM basic flowfield is found to be controlled by Van Wie empirical limit. It is concluded that the ICFM basic flowfield can effectively design high-performance fixed-geometry intakes with overboard spillage, demonstrating excellent performance and startability across a wide range of Mach numbers.
Musa et al. (Wed,) studied this question.