Air-Breathing Missile Thrust Measurement

Award Information
Agency:
Department of Defense
Branch
Army
Amount:
$119,980.00
Award Year:
2010
Program:
SBIR
Phase:
Phase I
Contract:
W31P4Q-10-C-0149
Agency Tracking Number:
A093-134-0236
Solicitation Year:
2009
Solicitation Topic Code:
A09-134
Solicitation Number:
2009.3
Small Business Information
Combustion Research and Flow Technology,
6210 Kellers Church Road, Pipersville, PA, 18947
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
929950012
Principal Investigator:
Sanford Dash
President & Chief Scientist
(215) 766-1520
dash@craft-tech.com
Business Contact:
Brian York
Principal Scientist & Treasurer
(215) 766-1520
cliffb@adatech.com
Research Institution:
n/a
Abstract
Innovative approaches to make direct measurements of thrust/drag forces on scramjet inlets will be designed, constructed, and demonstrated in this Phase I program for use in hypersonic shock tunnel facilities. Two force measurements will be made. The first is a local skin friction measurement, that in conjunction with CFD, can help predict integrated drag values. Skin friction gages will be modified/calibrated for use in the shock tunnel and will provide validation of the correlation used to obtain skin friction from a Reynolds analogy formulation, still needed for high resolution since numerous heat transfer gages can be implemented but only several skin friction gages. Innovative surface interpolation techniques will be utilized in integrating the forces. The second technique is a global force measurement that provides net model thrust and which will be configured to work with the ASET vehicle geometry. On-board recording devices are required here to isolate the test model. Substantive CFD support for experimental planning and for proof of concept validation is a key component of this proposed effort.

* information listed above is at the time of submission.

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