Parametric Experimental Studies on Supersonic Flow Unsteadiness over a Hemispherical Spiked Body-Reference-Cited by-同舟云学术

Parametric Experimental Studies on Supersonic Flow Unsteadiness over a Hemispherical Spiked Body

Published:2020-08 Issue:8 Volume:58 Page:3446-3463
ISSN:0001-1452
Container-title:AIAA Journal
language:en
Short-container-title:AIAA Journal

Author:

Sahoo Devabrata¹,Karthick S. K.¹,Das Sudip²,Cohen Jacob¹

Affiliation:

1. Technion—Israel Institute of Technology, Haifa 3200003, Israel

2. Birla Institute of Technology, Mesra 835 215, Jharkand, India

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Reference47 articles.

1. PilandR. O.PutlandL. W. “Zero-Lift Drag of Several Conical and Blunt Nose Shapes Obtained in Free Flight at Mach Number of 0.7 to 1.3,” NACA RM L54A27, 1954, https://digital.library.unt.edu/ark:/67531/metadc62594/.

2. JonesJ. “Flow Separation from Rods Ahead of Blunt Noses at Mach Number 2.72,” NACA RM L52E05a, 1952, https://ntrs.nasa.gov/search.jsp?R=19930087040.

3. AllenH. J.EggersA. J. Jr. “A Study of the Motion and Aerodynamic Heating of Ballistic Missiles Entering the Earth’s Atmosphere at High Supersonic Speeds,” NACA TR-1381, Jan. 1958, https://ntrs.nasa.gov/search.jsp?R=19930091020.

4. Experimental Investigations of Hypersonic Flow over Highly Blunted Cones with Aerospikes

5. CrawfordD. H. “Investigation of Flow over a Spiked Nose Hemisphere-Cylinder at Mach Number of 6.8,” NASA TN-D-118, 1959, https://catalog.hathitrust.org/Record/011447845.

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