@prefix rdf: <http://www.w3.org/1999/02/22-rdf-syntax-ns#> .
@prefix rdfs: <http://www.w3.org/2000/01/rdf-schema#> .
@prefix xsd: <http://www.w3.org/2001/XMLSchema#> .
@prefix owl: <http://www.w3.org/2002/07/owl#> .
@prefix constant: <http://qudt.org/vocab/constant/> .
@prefix dc: <http://purl.org/dc/elements/1.1/> .
@prefix dcterms: <http://purl.org/dc/terms/> .
@prefix prov: <http://www.w3.org/ns/prov#> .
@prefix qkdv: <http://qudt.org/vocab/dimensionvector/> .
@prefix quantitykind: <http://qudt.org/vocab/quantitykind/> .
@prefix qudt: <http://qudt.org/schema/qudt/> .
@prefix si-quantity: <https://si-digital-framework.org/quantities/> .
@prefix skos: <http://www.w3.org/2004/02/skos/core#> .
@prefix unit: <http://qudt.org/vocab/unit/> .
@prefix vaem: <http://www.linkedmodel.org/schema/vaem#> .
@prefix voag: <http://voag.linkedmodel.org/schema/voag#> .

quantitykind:SpecificImpulse
  a qudt:QuantityKind ;
  dcterms:description "The impulse produced by a rocket divided by the mass $mp$ of propellant consumed. Specific impulse ${I_{sp}}$ is a widely used measure of performance for chemical, nuclear, and electric rockets. It is usually given in seconds for both U.S. Customary and International System (SI) units.  The impulse produced by a rocket is the thrust force $F$ times its duration $t$ in seconds. $I_{sp}$ is the thrust per unit mass flowrate, but with $g_o$, is the thrust per weight flowrate. The specific impulse is given by the equation: $I_{sp} = \\frac{F}{\\dot{m}g_o}$."^^qudt:LatexString ;
  qudt:hasDimensionVector qkdv:A0E0L0I0M0H0T1D0 ;
  qudt:informativeReference "http://www.grc.nasa.gov/WWW/K-12/airplane/specimp.html"^^xsd:anyURI ;
  rdfs:isDefinedBy <http://qudt.org/3.2.1/vocab/quantitykind> ;
  rdfs:label "Specific Impulse"@en ;
  rdfs:seeAlso quantitykind:MassFlowRate .