Heat Transfer to a Full-coverage Film-cooled Surface with 30 ̊slant-hole Injection

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National Aeronautics and Space Administration, 1976 - Boundary layer - 231 pages

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Contents

1
1
Literature Review
7
Chapter
13

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Heat transfer to a full-coverage film-cooled surface with 30 ̊slant-hole ...
Michael E. Crawford,William Morrow Kays,R. J. Moffat
Snippet view - 1976

Common terms and phrases

01 TINF afterplate blowing ratio blowing region blowing row BLOWN SECTION boundary layer CATA Choe CM DEH2 CM UINF CM VISC coolant data from Figure data set DEG C TPLATE DEG C XVC DEG C Y(CM DEL2 DISCRETE HCLE RIG DISCRETE HOLE downstream DREEN enthalpy thickness Reynolds equation experimental F T2 THETA full-coverage film cooling heat flux heat transfer heat transfer coefficient heated starting length hole spacing initial boundary layer initial conditions injectant temperature KG/M3 CP LINEAR SUPERPOSITION M/S VISC M2/S DELI M2/S PR mixing-length Prediction preplate RATIO RUN ReA2 recovery region Red2 replotted versus enthalpy rows of holes secondary air shear stress SPANWISE PROFILE spanwise-averaged STANTON NUMBER DATA STANTON NUMBER RATIO T(DEG TACB TADB TBAR TBAR TBAR temperature profiles thermal boundary layer thermocouple thickness Reynolds number transpiration cooling tubes UNCERTAINTY versus enthalpy thickness wattmeter Y/DEL U(M/S Y+ U+ Y(CM

Bibliographic information

TitleHeat Transfer to a Full-coverage Film-cooled Surface with 30 ̊slant-hole Injection
NASA contractor report
AuthorsMichael E. Crawford, William Morrow Kays, R. J. Moffat
ContributorsUnited States. National Aeronautics and Space Administration, Stanford University
PublisherNational Aeronautics and Space Administration, 1976
Length231 pages
  
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