Drag force on quasi-axisymmetric scramjets at various flight Mach numbers: theory and experiment

The net axial force on a non-fuelled quasi-axisymmetric scramjet model designed for operation at Mach 6 was measured in the T4 Stalker tube at The University of Queensland using a single-component stress wave force balance. The design used was a variant of a model that was tested previously at Mach 6. The new model was equipped with a modified thrust nozzle that was designed to improve the performance of the nozzle. Tests were performed to measure the drag force on the model for Mach 6, Mach 8 and Mach 10 shock tunnel nozzles for a range of flow conditions. The nozzle-supply enthalpy was varied from 3 to 10 MJ/kg and the nozzle-supply pressure from 35 to 45 MPa. For the test model, the drag coefficient increased with increasing nozzle-supply enthalpy. The test results are compared with a force prediction method based on simple hypersonic theories and three-dimensional CFD. The test results are in good agreement with the predictions over the wide range of conditions tested. The re-designed model has a more efficient nozzle but this comes at the expense of increased drag associated with the modifications required for the cowl. The results indicate that this type of vehicle design is not likely to be suitable for flight above Mach 8.

[1]  Allan Paull,et al.  Scramjets and shock tunnels—The Queensland experience , 2005 .

[2]  S. G. Mallinson,et al.  An experimental investigation of hypervelocity flow in a conical nozzle , 1996 .

[3]  S R Sanderson,et al.  Drag balance for hypervelocity impulse facilities , 1991 .

[4]  R. G. Morgan,et al.  Transition of compressible high enthalpy boundary layer flow over a flat plate , 1994, The Aeronautical Journal (1968).

[5]  Peter A. Jacobs,et al.  Background oriented schlieren for flow visualisation in hypersonic impulse facilities , 2007 .

[6]  Lucien Z. Dumitrescu,et al.  Shock Waves @ Marseille III , 1995 .

[7]  J. R. Moselle,et al.  Computer program for the numerical solution of nonequilibrium expansions of reacting gas mixtures , 1966 .

[8]  David J. Mee,et al.  Dynamic strain measurement using piezoelectric polymer film , 1996 .

[9]  Sean Tuttle,et al.  Developing a stress wave thrust balance for a hypersonic shock tunnel , 1997, ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities.

[11]  David J. Mee,et al.  Dynamic calibration of force balances for impulse hypersonic facilities , 2003 .

[12]  R. J. Stalker,et al.  The Free-Piston Shock Tube , 1966 .

[13]  Russell R. Boyce,et al.  Mass spectrometric measurements of driver gas arrival in the T4 free-piston shock-tunnel , 2005 .

[14]  R. Stalker.  Waves and thermodynamics in high Mach number propulsive ducts , 1991 .

[15]  Ryan P. Starkey,et al.  Critical Design Issues for Airbreathing Hypersonic Waverider Missiles , 2001 .

[16]  M. H. Bertram,et al.  Engineering prediction of turbulent skin friction and heat transfer in high-speed flow , 1974 .

[17]  C. Horstman,et al.  Hypersonic Crossing Shock-Wave/Turbulent- Boundary-Layer Interactions , 1993 .

[18]  Katsuyoshi Tanimizu.  Nozzle optimization study and measurements for a quasi-axisymmetric scramjet model , 2008 .

[19]  T. Grundy,et al.  Progress in Astronautics and Aeronautics , 2001 .

[20]  Allan Paull,et al.  Scramjet Lift, Thrust and Pitching-Moment Characteristics Measured in a Shock Tunnel , 2006 .

[21]  Roy J. Hartfield,et al.  Scramjet missile design using genetic algorithms , 2006, Appl. Math. Comput..

[22]  D. B. Spalding,et al.  The drag of a compressible turbulent boundary layer on a smooth flat plate with and without heat transfer , 1964, Journal of Fluid Mechanics.

[23]  Peter A. Jacobs,et al.  Use of Argon-Helium Driver-Gas Mixtures in the T4 Shock Tunnel , 1995 .

[24]  T. Streit,et al.  Approximate Heat Transfer Methods for Hypersonic Flow in Comparison with Results Provided by Numerical Navier-Stokes Solution , 1994 .

[25]  Allan Paull,et al.  Experiments on supersonic combustion ramjet propulsion in a shock tunnel , 1995, Journal of Fluid Mechanics.