Performance of a 2D-CD nonaxisymmetric exhaust nozzle on a turbojet engine at altitude | Zendy

David M Straight | Zendy; R. R. Cullom | Zendy

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Performance of a 2D-CD nonaxisymmetric exhaust nozzle on a turbojet engine at altitude

Author(s) -

David M Straight,

R. R. Cullom

Publication year - 1982

Publication title -

24th joint propulsion conference

Language(s) - English

Resource type - Conference proceedings

DOI - 10.2514/6.1982-1137

Subject(s) - turbojet , nozzle , aerospace engineering , automotive engineering , aeronautics , environmental science , acoustics , engineering , physics

Baseline thrust and cooling data obtained with a 2D-CD versatile research exhaust nozzle mounted on a turbojet engine in an altitude chamber are presented. The tests covered a range of nozzle pressure ratios, nozzle pressure ratios, nozzle throat areas, and internal expansion area ratios. The thrust data obtained show good agreement with theory and scale model results after correcting the data for leakage and bypass cooling flows. Additional work is needed to improve predictability of cooling performance.

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