1. Hot Flow Data (Averaged) Symbol Configuration
2. Fig. D14 Comparisonofthe averagebase pressuredatafrom hotflow and coldflow testswithSpaceShuttle (STS-1)andSaturnV/SI-Cflight-test resultsasafunctionof Machnumber.SaturnV/S-I Candshuttle/SRBbasepressuresseemtobeinthesame ballpark.Wind-tunneltestsusedGoethert-BarnesjetsimilarityrulesfoundinAEDC TR-58-12.Data adapted from LMSC-HREC-D225152,June 1971, Fig. 3.3-3.13.Test pointsofnonflight configurations have beenremoved.
3. where the parameters aredefined inFig. D8 and the three empirical factors a, b, andcareweakfunctions ofvehiclegeometry.Baseduponthemeasurementstaken and the analysis, a varied around 0.25,b took values between 0.5 and 1.0 (with 0.5being abetterfitforasingleaftbody andnozzle)and 1.0fitting inthe 0.9-3.38 Mach-number rangeformultiple nozzles. Late in the hot gas testprogram it was determinedthattheadditionalfunction of(Tc/Ttoo)cwiththeempiricalfactorcfor temperaturecorrectionsisrequiredtofully correlatethedata.Thesedatacametoo late in the shuttlebase flow program to impact any testing; furthermore, the few hotgasjet datapointsweretoo spottyto extrapolateto allMachnumbers andvehiclebaseconfigurations.Itwasdeterminedthattheeffect ofnotincorporatingthe x1fl 5 4.0
4. 'Roberts, B. B., Wallace, R. O., and Sims, J. L."Plume Base Flow Simulation Technology,"Shuttle Performance: LessonsLearned, NASA CP-2283,PartI,Washington,DC, March 1983.