SCALING IN A DUCTED ROCKET COMBUSTOR IRRDP-DREV-TN-9602(1)

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Authors
  1. Stowe, R.A.
Corporate Authors
Defence Research Establishment Valcartier, Valcartier QUE (CAN)
Abstract
The Defence Research Establishment Valcartier (DREV) in Canada and the TNO Prins Maurits Laboratory (TNO-PML) in the Netherlands have undertaken a collaborative activity known as the Integral Rocket Ramjet Demonstration Program (IRRDP) to demonstrate several of the key technologies of an airbreathing propulsion unit for a medium range air-launched missile. An essential component of the airbreathing propulsion system is the ducted rocket combustor, and as part of its development, experiments are to be done at TNO's direct-connect combustion test facility using existing subscale combustor hardware. Test results will therefore have to be scaled up to the larger "full-size" combustor, and one such technique to do this is "PD-scaling". PD-scaling requires that geometric similarity be maintained, and that the product of the static pressure in the combustor and the length scale (diameter) be held constant between the model and full-size (prototype) combustors. Inlet velocities, fuel type, air/fuel ratios, and inlet temperatures must also be kept constant. Assuming that the global reaction rate is second order and that heat losses through the combustor wall are not significant, then PD-scaling should allow test results from the subscale ducted rocket combustors to be extrapolated to the larger propulsion systems of interest. TRUNCATED
Keywords
Air breathing engines;Air breathing propulsion;Combustors;Booster rocket engines;Supersonic combustor ramjet engines;Ducted rocket engines
Report Number
DREV-9733 — Technical Memorandum
Date of publication
01 Feb 1998
Number of Pages
34
DSTKIM No
98-00913
CANDIS No
507598
Format(s):
Hardcopy;Document Image stored on Optical Disk

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