Thrust Augmenter Research Methods

Aerospace propulsion engineering


Golubev V. A.1, Monakhova V. P.2*

1. Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia
2. ,



Results of design-theoretical and experimental research of ejector thrust augmenter characteristics brought. Values of ejection coefficient η = 4.64 and propulsion increase of 50% (propulsion augmentation coefficient δ≅1.5) relative length of ejection channel of L = 6.7 and considering area relation at ejector inlet of were α = 0.042 obtained.

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