RE: How to Correct Measured Thrust for Density Altitude?
Let me try if I can help…
Considering Thrust (T)= mass flow rate * exhaust velocity
T = density * volume flow rate * velocity
T = density * A * (D/t) * velocity
T =density * A * velocity ^2
Consider test stand thrust T1 = density1 * A1 * velocity1 ^2
and test 2 thrust, T2 = density2 * A2 * velocity2 ^2
Same engine, Area A1 = A2 therefore
T2/T1 = density2 * velocity2^2/( density1 * velocity1^2)
T2 = T1 * [ density2 * velocity2^2/( density1 * velocity1^2)]
T2 = T1 * (density2/density1) * (velocity2/velocity1)^2
If T1 = T2 then
density1 * velocity1^2 = density2 * velocity2^2