Books on the topic 'Film cooling'

Aerssens, S. E. E. Modelling of two-dimensional film cooling. Manchester: UMIST, 1994.

Simon, Frederick F. Jet model for slot film cooling with effect of free-stream and coolant turbulence. Cleveland, Ohio: Lewis Research Center, 1986.

Nan-Suey, Liu, and NASA Glenn Research Center, eds. Film cooling flow effects on post-combustor trace chemistry. Cleveland, Ohio: National Aeronautics and Space Administration, Glenn Research Center, 2003.

Garg, Vijay Kumar. Effect of coolant temperature and mass flow on film cooling of turbine blades. [Washington, D.C: National Aeronautics and Space Administration, 1997.

Olsen, George C. Hydrogen film cooling with incident and swept-shock interactions in a Mach 6.4 nitrogen free stream. Hampton, Va: Langley Research Center, 1995.

Acharya, Sumanta. Large eddy simulations and turbulence modeling for film cooling. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 1999.

Ward, S. C. Validation of a CFD model for predicting film cooling performance. Washington, D. C: American Institute of Aeronautics and Astronautics, 1993.

Garg, Vijay Kumar. Leading edge film cooling effects on turbine blade heat transfer. [Washington, DC]: National Aeronautics and Space Administration, 1995.

J, Bruckner R., Smith F. A, and United States. National Aeronautics and Space Administration., eds. Application of thin-film thermocouples to localized heat transfer measurements. [Washington, DC]: National Aeronautics and Space Administration, 1995.

Lepicovsky, J. Application of thin-film thermocouples to localized heat transfer measurements. [Washington, DC]: National Aeronautics and Space Administration, 1995.

Lepicovsky, J. Application of thin-film thermocouples to localized heat transfer measurements. [Washington, DC]: National Aeronautics and Space Administration, 1995.

Heidmann, James D. Coarse grid modeling of turbine film cooling flows using volumetric source terms. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2001.

1934-, Hoffman Joe D., and United States. National Aeronautics and Space Administration., eds. The prediction of nozzle performance and heat transfer in hydrogen/oxygen rocket engines with transpiration cooling, film cooling, and high area ratios. [Washington, DC]: National Aeronautics and Space Administration, 1994.

1934-, Hoffman Joe D., and United States. National Aeronautics and Space Administration., eds. The prediction of nozzle performance and heat transfer in hydrogen/oxygen rocket engines with transpiration cooling, film cooling, and high area ratios. [Washington, DC]: National Aeronautics and Space Administration, 1994.

L, Rigby David, and Lewis Research Center, eds. Heat transfer on a film-cooled blade: Effect of hole physics : prepared under contract NAS3-27571. [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, 1998.

L, Rigby David, and Lewis Research Center, eds. Heat transfer on a film-cooled blade: Effect of hole physics : prepared under contract NAS3-27571. [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, 1998.

L, Rigby David, and Lewis Research Center, eds. Heat transfer on a film-cooled blade: Effect of hole physics : prepared under contract NAS3-27571. [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, 1998.

Kaisuwan, Pisut. Effect of vortex circulation on injectant from a single film-cooling hole and a row of film-cooling holes in a turbulent boundary layer, part 2: injection beneath the vortex upwash. Monterey, Calif: Naval Postgraduate School, 1989.

Craig, Douglas William. Effect of vortex circulation on injectant from a single film-cooling hole and a row of film-cooling holes in a turbulent boundary layer: Part 1: injection beneath the vortex downwash. Monterey, Calif: Naval Postgraduate School, 1989.

D, Hylton L., and United States. National Aeronautics and Space Administration., eds. The Effects of leading edge and downstream film cooling on turbine vane heat transfer. [Washington, DC]: National Aeronautics and Space Administration, 1989.

United States. National Aeronautics and Space Administration., ed. A numerical study of the effect of wake passing on turbine blade film cooling. [Washington, D.C.]: National Aeronautics and Space Administration, 1995.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Experimental study of vane heat transfer and film cooling at elevated levels of turbulence. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1996.

United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Experimental study of vane heat transfer and film cooling at elevated levels of turbulence. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1996.

R, Karr Gerald, and United States. National Aeronautics and Space Administration., eds. Analysis of film cooling in rocket nozzles: Final report, contract #NAG8-212, task no. 3. Tuscaloosa, Ala: University of Alabama, College of Engineering, Bureau of Engineering Research, 1993.

K, Furuhama, and United States. National Aeronautics and Space Administration, eds. Film cooling on a convex wall: Heat transfer and hydrodynamic measurements for full and partial coverage. [Washington, D.C.]: National Aeronautics and Space Administration, 1985.

Williams, Warren W. Effects of an embedded vortex on a single film-cooling jet in a turbulent boundary layer. Monterey, California: Naval Postgraduate School, 1988.

Garg, Vijay Kumar. Effect of velocity and temperature distribution at the hole exit on film cooling of turbine blades. [Washington, DC]: National Aeronautics and Space Administration, 1995.

E, Gaugler R., and United States. National Aeronautics and Space Administration., eds. Effect of velocity and temperature distribution at the hole exit on film cooling of turbine blades. [Washington, D.C: National Aeronautics and Space Administration, 1997.

United States. National Aeronautics and Space Administration., ed. Gas-jet and tangent-slot film cooling tests of a 12.5⁰ cone at Mach number of 6.7. [Washington, DC]: National Aeronautics and Space Administration, 1988.

United States. National Aeronautics and Space Administration., ed. Gas-jet and tangent-slot film cooling tests of a 12.5⁰ cone at Mach number of 6.7. [Washington, DC]: National Aeronautics and Space Administration, 1988.

Philip, Poinsatte, NASA Glenn Research Center, and U.S. Army Research Laboratory., eds. Experimental heat transfer and bulk air temperature measurements for a multipass internal cooling model with ribs and bleed. Cleveland, Ohio: National Aeronautics and Space Administration, Glenn Research Center, 2000.

Center, NASA Glenn Research, ed. Heat transfer on a film-cooled rotating blade. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 1999.

Ramsey, Anthony Eldorado. A study of film cooling downstream of one and two rows of holes oriented in spanwise/normal planes. Monterey, Calif: Naval Postgraduate School, 1992.

Wigle, James Michael. Heat transfer, adiabatic effectiveness and injectant distribution downstream of single and double rows of film-cooling holes with compound angles. Monterey, Calif: Naval Postgraduate School, 1991.

J, Nowak Robert, and United States. National Aeronautics and Space Administration., eds. Hydrogen file cooling with incident and swept-shock interactions in a Mach 6.4 nitrogen free stream. [Washington, DC]: National Aeronautics and Space Administration, 1995.

Faghri, Amir. Numerical and experimental analysis of a thin liquid film on a rotating disk related to development of a spacecraft absorption cooling system. [Washington, DC]: National Aeronautics and Space Administration, 1990.

Ciriello, Salvatore. Heat transfer, adiabatic effectiveness and injectant distributions downstream of single and double rows of film-cooling holes with simple and compound angles. Monterey, Calif: Naval Postgraduate School, 1991.

United States. National Aeronautics and Space Administration., ed. [An analysis of gamma ray burst time histories]: Final report. Huntsville, AL: University of Alabama in Huntsville, Summer Faculty Fellowship Research Continuation Program, 1994.

United States. National Aeronautics and Space Administration., ed. [FDNS code to predict wall heat fluxes or wall temperatures in rocket nozzles]: Final report. Huntsville, AL: University of Alabama in Huntsville, 1993.

Jackson, Stephen Mark. Heat transfer, adiabatic effectiveness and injectant distributions downstream of single rows and two staggered rows of film-cooling holes with simple and compound angles. Monterey, Calif: Naval Postgraduate School, 1991.

Woodbury, Keith. FNAS/Summer faculty Fellowshop Research Continuation Program task #3 entitled analysis of film cooling in rocket nozzle: Semi-annual report, January 17, 1992 - October 17, 1992. [Washington, DC: National Aeronautics and Space Administration, 1992.

United States. National Aeronautics and Space Administration, ed. Development of computer models for correlating data of film cooling of nose cone under hypersonic flow: Semi-annual status report (April 1, 1986 to September 30, 1986). Greensboro, NC: North Carolina A&T State University, 1987.

Spectrally selective surfaces for heating and cooling applications. Bellingham, Wash., USA: SPIE Optical Engineering Press, 1989.

Ju, Y. Sungtaek. Microscale heat conduction in integrated circuits and their constituent films. Boston: Kluwer Academic, 1999.

Ju, Y. Sungtaek. Microscale heat conduction in integrated circuits and their constituent films. Boston: Kluwer Academic, 1999.

H, Wagner Joel, and United States. National Aeronautics and Space Administration., eds. Heat transfer experiments in the internal cooling passages of a cooled radial turbine rotor. [Washington, D.C.]: National Aeronautics and Space Administration, 1996.

H, Wagner Joel, and United States. National Aeronautics and Space Administration., eds. Heat transfer experiments in the internal cooling passages of a cooled radial turbine rotor. [Washington, D.C.]: National Aeronautics and Space Administration, 1996.

U.S. Nuclear Regulatory Commission. Office of Nuclear Regulatory Research and Laboratory for Thermal-Hydraulics (Paul Scherrer Institut), eds. Development, implementation, and assessment of specific closure laws for inverted-annular film-boiling in a two-fluid model. Washington, DC: Office of Nuclear Regulatory Research, U.S. Nuclear Regulatory Commission, 1996.

150 years of cool law. Dayton, Ohio: High View Library, 2003.

National Aeronautics and Space Administration (NASA) Staff. Analysis of Film Cooling in Rocket Nozzles. Independently Published, 2018.