Hello guys
I'm confused about Concorde Nozzle a bit.
-1.During the transonic about M1.1 the Seconcdary Nozzle position at 0 degree mean that the exhaust between Primary and Secondary nozzle have enough static preesure due to high speed air that vent around engine. This is correct or not?
-2.Then the exhaust gas enter the divergence sction [Secondar Nozzle] which accelerate the exhaust gas to supersonic which cause by expansive shock.This is corrected or not?
-3.The exhaust system of the Concorde should produce more thust while it in transonic than during take off because during trasonic the exhaust can acclerate to supersonic speed without overexapnasion problem. This is correct or not?
Thanks for reply
and sorry for bad english.
I'm confused about Concorde Nozzle a bit.
-1.During the transonic about M1.1 the Seconcdary Nozzle position at 0 degree mean that the exhaust between Primary and Secondary nozzle have enough static preesure due to high speed air that vent around engine. This is correct or not?
-2.Then the exhaust gas enter the divergence sction [Secondar Nozzle] which accelerate the exhaust gas to supersonic which cause by expansive shock.This is corrected or not?
-3.The exhaust system of the Concorde should produce more thust while it in transonic than during take off because during trasonic the exhaust can acclerate to supersonic speed without overexapnasion problem. This is correct or not?
Thanks for reply
and sorry for bad english.
