Gruhn, Patrick and Gülhan, Ali (2011) Experimental investigation of a hypersonic inlet with and without sidewall compression. Journal of Propulsion and Power, Vol. 27 (No. 3). AIAA - American Institute of Aeronautics and Astronautics.
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The inlet of a Mach 8 cruise vehicle has been experimentally investigated in a hypersonic blow down wind tunnel with test times of up to 30s. Two test series have been carried out, the first one with a two-dimensional inlet configuration and the second one with the inlet featuring additional side-wall compression. The objective of the tests was to determine the performance of the inlet at on- and off-design conditions, i.e. at angle of attack and angle of yaw. Additionally, the starting behavior of the inlet has been determined, i.e. the contraction ratio at which the inlet starts. Results were interpreted from schlieren visualizations, IR thermography, static and Pitot pressure readings and mass flow measurements. The off-design investigation of both inlet configurations revealed the sensitivity of the inlet towards a cowl shock induced separation on the second compression ramp. If the cowl shock was not ensured to fall into the bleed duct behind the second ramp, no inlet flow could be established. The comparison of starting contraction ratios showed the advantage of the inlet with side-wall compression, i.e. the inlet with sidewall compression starts at higher contraction ratios.
|Title:||Experimental investigation of a hypersonic inlet with and without sidewall compression|
|Journal or Publication Title:||Journal of Propulsion and Power|
|In Open Access:||No|
|In ISI Web of Science:||Yes|
|Publisher:||AIAA - American Institute of Aeronautics and Astronautics|
|Keywords:||Scramjet, Hypersonic Propulsion, Inlet, LAPCAT|
|HGF - Research field:||Aeronautics, Space and Transport (old)|
|HGF - Program:||Aeronautics|
|HGF - Program Themes:||other|
|DLR - Research area:||Aeronautics|
|DLR - Program:||L - no assignement|
|DLR - Research theme (Project):||L -- no assignement|
|Institutes and Institutions:||Institute of Aerodynamics and Flow Technology > Supersonic and Hypersonic Technology|
|Deposited By:||Patrick Gruhn|
|Deposited On:||27 Jun 2011 08:46|
|Last Modified:||07 Feb 2013 20:34|
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