Abdel-Jawad M M, Mee D J, Morgan R G, Jacobs, P A, Philpot J A 2001 Transient force measurements at superorbital speeds.Proc. 23rd Int. Symp. on Shock Waves (ed.) F K Lu, Fort Worth, TX, pp. 515–521
Alan P, Kennith L G 1965High-speed wind tunnel testing (New York: John Wiley & Sons)
Anderson J D Jr 1989Hypersonic and high temperature gas dynamics (Series in Aeronautical and Aerospace Engineering) (New York: McGraw-Hill)
Brian R H, John N P 1997 High enthalpy aerothermodynamics of a Mars entry vehicle Part 1: Experimental results,J. Spacecr. Rockets 34: 449–456
Cook W J, Felderman E J 1966 Reduction of data from thin film heat transfer gauge: A concise numerical technique.AIAA J. 4: 561–562
Fay J A, Riddell F R 1958 Theory of stagnation point heat transfer in dissociated air.J. Aeronaut. Sci.
Hollis B R 1995 User’s manual for the one-dimensional hypersonic experimental aero thermodynamic (1DHEAT) data reduction code. NASA CR-4961
Hollis B R, Perkins J N 1996 High enthalpy and perfect gas heating measurements on a blunt cone.J. Spacecr. Rockets
Jagadeesh G 1997Experimental investigations of the flow-fields around large angle blunt cones flying at hypersonic Mach number. Ph D thesis, Department of Aerospace Engineering, Indian Institute of Science, Bangalore
Jagadeesh G, Reddy N M, Nagashetty K, Reddy, K P J 2000 Fore body convective hypersonic heat transfer measurements over large angle blunt cones.J. Spacecr. Rockets 37: 137–139
Jessen C, Gronig H 1989 A new principle for a short-duration six component balance.Exp. Fluids
Joshi M V, Reddy N M 1986 Aerodynamic force measurements over missile configurations in IISc shock tunnel at M∞
= 5.5.Exp. Fluids
Lee J Y, Lewis M J 1993 Numerical study of the flow establishment time in hypersonic shock tunnels.J Spacecr. Rockets 30: 152–163
Mee D J, Daniel W J T, Simmons J M 1996 Three-component force balance for flows of millisecond duration.AIAA J. 34: 590–595
Mee D J 1993 Uncertainties analysis of conditions in test section of the T4 shock tunnel, Research Report No: 4/93, Center for Hypersonics, University of Queensland, Australia
Naumann K W, Ende H, Mathieu G, George A 1993 Millisecond aerodynamic force measurement with side-jet model in ISL shock tunnel.AIAA J. 31: 1068–1074
Olivier H, Gronig H 1995 Hypersonic model testing in a shock tunnel.AIAA J. 33: 262–265
Peter F I, Donn B K 1987 High-speed aerodynamics of several blunt-cone configurations.J. Spacecr. Rockets 24: 127–132
Raju C, Reddy N M 1990 Aerodynamic force measurements over missile configurations in IISc shock tunnel at M∞
= 3.85 and 9.15.Exp. Fluids
Reddy N M 1980 Heating rate measurements over 30‡ and 40‡ (half-angle) blunt cones in air and helium in the Langley expansion tube facility. NASA TM-80207
Reddy N M 1985 Development of a three-component balance for use in a shock tunnel, High Enthalpy Aerodynamic Report No. 85 HEA 2 Serial No. 04, Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India
Sahoo N, Mahapatra D R, Jagadeesh G, Gopalakrishnan S, Reddy K P J 2002 Aerodynamic force measurements on 60‡ apex angle blunt cones flying at Mach 5.75 using a three-component accelerometer balance.AIAA Paper 2002-5204
Sahoo N, Mahapatra D R, Jagadeesh G, Gopalakrishnan S, Reddy K P J 2003 An accelerometer balance system for measurement of aerodynamic force coefficients over blunt bodies in a hypersonic shock tunnel.Meas. Sci. Technol.
Sahoo N 2003Simultaneous measurement of aerodynamic forces and convective surface heat transfer rates for large angle blunt cones in hypersonic shock tunnel, Ph D thesis, Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India.
Schultz D L, Jones T V 1973 Heat transfer measurements in short-duration hypersonic facilities. AGARDograph No. 165.
Srinivasa P 1991Experimental investigations of hypersonic flow over a bulbous heat shield at Mach number 6. Ph D thesis, Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India.
Stewart D A, Chen Y K 1994 Hypersonic convective heat transfer over 140‡ blunt cones in different gases.J. Spacecr. Rockets 31: 735–743
Truitt R W 1959Hypersonic aerodynamics (New York: Ronald Press)
Vidal R J 1956 Model instrumentation techniques for heat transfer and force measurements in a hypersonic shock tunnel. Cornell Aeronautical Laboratory Report, WADC TN 56–315
Viren M, Saravanan S, Jagadeesh G, Reddy K P J 2002 Aerodynamic drag reduction using aero-spikes for large angle blunt cone flying at hypersonic Mach number. AIAA Paper 2002-2709
Viren M 2003Investigations of aero-spike induced flow field modifications around a large angle blunt cone flying at hypersonic Mach number. Ph D thesis, Department of Aerospace Engineering, Indian Institute of Science, Bangalore