What is the approximate thrust at sea level for a C-130J Hercules? I am looking for the approximate thrust of a C-130J Hercules under ISA sea level conditions. Also the efficiency of its propeller would be of help.
An answer to this question would really help my calculations for an assignment, so I don't have to guess values. If you could direct me to your sources as well, that would be highly appreciated.
The C-130J is equipped with  Rolls Royce AE-2100 D3 engines and the propellers would be the 6-bladed Dowty R391.
Okay guys, so I found some data from an old service publication from Lockheed. It says that the new C-130J propulsion system under standard conditions and flying 80 kts is rated &quot;4,637 SHP, but produces 10,200 lbs&quot;.
So using the equation for thrust available for a propeller aircraft I get:
$T_a = \frac{\eta \cdot P_s }{V}$
with:
$T_a = $Thrust available
$\eta =$propeller efficiency
$P_s =$shaft power
$V=$air speed
$\eta = \frac{T_a \cdot V}{P_s}$
$\eta = \frac{10200 \textrm{lbf} \cdot 80 \textrm{kts}[ \textrm{aka. }135 \textrm{ ft/s}]}{4637 \textrm{shp} [\cdot 550 \textrm{ conversion}]}$
$\eta = 0.54$
This seems quite low but its what I got for anyone wondering. The service publication I got the info from is this:
https://www.sikorskyaerospace.com/content/dam/lockheed-martin/aero/documents/sustainment/csc/service-news/sn-mag-v21-v30/V25N03.pdf