Construction and Commissioning of a Hypersonic Test Facility

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Authors
  1. Mailhot, S.
  2. Stowe, R.
  3. Farinaccio, R.
  4. deChamplain, A.
  5. Couture, D.
  6. Verreault, J.
Corporate Authors
Defence R&D Canada - Valcartier, Valcartier QUE (CAN);Laval Univ, Quebec QUE (CAN) Dept of Mechanical Engineering
Abstract
For access to space, rockets are the current propulsion system of choice. However, by exploiting airbreathing propulsion for at least part of the flight, significant improvements in performance are possible resulting in increased payload for a given amount of fuel. For hypersonic flight speeds, considered to be beyond Mach 5, the airbreathing propulsion system having received the most attention is the supersonic combustion ramjet, or scramjet. In a conventional scramjet, the intake air is compressed from the flight speed to a slower, but still supersonic speed. At the start of the combustor, the fuel is injected to mix and react with the air. Because the fuel must mix with the supersonic air to form a combustible mixture, the combustor can be quite long. One concept showing great promise but having received relatively little attention is the shock-induced combustion ramjet, or shcramjet (Figure 1) [1]. The shcramjet decouples the fuel injection and combustion processes by injecting the fuel ahead of the combustor from the forebody of the flight vehicle so that the fuel is well mixed with the air before it reaches the combustor. Upon reaching the combustor, the mixture crosses an oblique shock wave that raises its static temperature to greatly enhance the rate of reaction, thus significantly reducing combustor length and related mass, volume, and drag. In order to test different prototypes at hypersonic flight conditions, the Propulsion Group at DRDC Valcartier is currently un
Report Number
DRDC-VALCARTIER-SL-2010-183 — Scientific Literature
Date of publication
01 May 2010
Number of Pages
6
DSTKIM No
CA034970
CANDIS No
534590
Format(s):
Electronic Document(PDF)

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