Can anyone help to find data or book on Isp for hybrid rocket engines using LOX as oxidizer?
I am interested to know Isp for LOX combinations with carbon, Al+HTPB, parafin, sugar and others.
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$\begingroup$ Book recommendations or questions asking for resources outside the site are considered off-topic. is there a specific question? Furthermore, have you read en.wikipedia.org/wiki/Liquid_rocket_propellant, especially the tables? $\endgroup$– PolygnomeJan 17, 2017 at 23:34
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2$\begingroup$ None of the propellants in that table correspond to those mentioned by OP. $\endgroup$– Russell BorogoveJan 18, 2017 at 4:04
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2$\begingroup$ spg-corp.com/hybrid-rocket-propulsion.html claims 340s for paraffin-LOX at 70:1, but I don't know if that's even plausible. $\endgroup$– Russell BorogoveJan 18, 2017 at 4:09
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Here's some information from Delft University with a table showing 275-300s specific impulses for various HTPB and PE hybrids.
Here's a nice hybrid overview paper with a broader table, giving LOX-carbon Isp 249s, LOX-HTPB/Al 40% Isp 274s, LOX-paraffin 281s. These figures are all for chamber pressure of 3.5MPa (~35 atmospheres), exhausting at sea level pressure, but expansion ratio not specified.
The closest thing in the latter table to sugar is cellulose, which gives 247s burned with gaseous oxygen. (Sucrose is C6H12O6, sorbitol is C6H14O6, cellulose C6H10O5.)
answered Jan 18, 2017 at 4:12