equations equal to each other and solve for the new surface temperature. The new
surface temperature would be 523.79 R compared to the original temperature of 1400 R.
By using my experimental results where there is an average of 1.5 times the enhancement
in heat transfer then the new surface temperature would be 963.33 R compared to 1400
R. For the pressure drop calculation an average temperature of the coolant which is
194.508 R will be used to calculate the properties and determine the pressure drop over a
2-foot length. The properties are as follows: Prandtl number is 0.785, the conductivity is
0.0116 lb/s-R, the density is 1.36 lb/ft3, and the viscosity is 1.13e-7 lb-s/ft2. Using the
definition of the Reynolds number the velocity is calculated to be 37.75 ft/s for a
Reynolds number of 1,000,000. Using the correlations for friction factor and pressure
drop as outlined in chapter 4 the expected pressure drop can be determined. This
expected pressure drop comes out to be 9.11 psi with a friction factor of 1.54. With my
experimental results of 3 psi at an expected 0.18 psi, then the pressure drop for this
system would be 151.78 psi with an expected of 9.11 psi. These numbers depict a
positive heat transfer enhancement even with my experimental results as well as minimal
pressure drop. However, these correlations and scaling based on my experimental results
need to be performed on exact dimensions of a cooling channel and with exact
specifications for that rocket engine that the cooling channel in question resides. When
this is completed a more accurate representation of what can be achieved with this idea of
metallic foam inserts used in the cooling channels will be shown. Also a more accurate
representation of how much pressure drop through these cooling passages can be
achieved.