The use of energy thickness in prediction of throat heat transfer in rocket nozzles /

Heat-transfer measurements on a blunt spherical-segment nose to a Mach number of 15.1 and flight performance of the rocket-propelled model to a Mach number of 17.8 /

Rumsey, Charles B.
Lee, Dorothy B.
Langley Research Center.

January 1959

"November 1959."Cover title.Includes bibliographical references (p. 17-18).Mode of access: Internet

Heat- and mass-transfer characteristics of an axial-flow liquid-core nuclear rocket employing radiation heat transfer /

Ragsdale, Robert G.
Donovan, Leo F.
Kascak, Albert F.
United States. National Aeronautics and Space Administration.

January 1967

Cover title."August 1967."Includes bibliographical references (p. 31-32).Mode of access: Internet

Dataset of the experimentally measured heat transfer in the throat region of liquid rocket engine thrust chambers

Marco Pizzarelli

August 2021

About 500 experimental heat transfer data taken from the open literature and relevant to the most th...

The use of energy thickness in prediction of throat heat transfer in rocket nozzle

Boldman, D. R.
Graham, R. W.

July 1969

Energy thickness in prediction of throat heat transfer in rocket nozzles using nozzle geometries and...

Estimation of Throat Heat Flux in Liquid Rocket Engines

Pierluigi Concio
Mario Tindaro Migliorino
Francesco Nasuti

January 2019

The problem of prediction of heat flux at throat of liquid rocket engines still constitutes a chall...

Experimental evaluation of heat transfer on a 1030:1 area ratio rocket nozzle /

Kacynski, Kenneth J.
Smith, Tamara A.
Pavli, Albert J.
Lewis Research Center.

January 1987

Prepared at Lewis Research Center."August 1987"--Cover.Includes bibliographical references (p. 24).M...

Theoretical investigation of radiant heat transfer in the fuel region of a gaseous nuclear rocket engine /

Kesten, A. S.
Krascella, N. L.

"January 1967"--cover.Includes bibliographical references.Prepared by United Aircraft Corporation.Mo...

An analysis of thermal radiation heat transfer in a nuclear-rocket nozzle /

Robbins, William H.
United States. National Aeronautics and Space Administration.

Cover title."January 1961."Propulsion systems, nuclear.Includes bibliographical references.Mode of a...

Heat transfer in a 60⁰ half-angle of convergence nozzle with various degrees of roughness /

Reshotko, Meyer.
Ehlers, Robert C.
Boldman, Donald R.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1970

Heat transfer in convergent-divergent nozzles with different values of wall roughness.Includes bibli...

EXPERIMENTAL DETERMINATION OF TEMPERATURE AND PRESSURE GRADIENTS IN ROCKET EXHAUSTS.

Herget, William F.
Levin, B. P.
Suarez-Alfonso, E.

January 1965

Supported by NASA, George C. Marshall Space Flight Center, Huntsville, Alabama.Author Institution: R...

Application of various techniques for determining local heat-transfer coefficients in a rocket engine from transient experimental data /

Liebert, Curt H.
Grant, Ronald W.
Hatch, James E.
Lewis Research Center.

January 1960

"NASA TN D-277.""Lewis Research Center, Cleveland, Ohio.""April 1960."Cover title.Includes bibliogra...

Numerical estimation of nozzle throat heat flux in oxygen-methane rocket engines

Concio, Pierluigi
Tindaro Migliorino, Mario
Bianchi, Daniele
Nasuti, Francesco

January 2022

The prediction of wall heat flux at the nozzle throat is of paramount importance in liquid rocket en...

Numerical approach for the estimation of throat heat flux in liquid rocket engines

Pierluigi Concio
Mario Tindaro Migliorino
Francesco Nasuti

January 2020

The problem of prediction of heat flux at throat of liquid rocket engines still constitutes a challe...

A comparison of stagnation-point heating in a rocket exhaust to that of actual flight /

Paris, Frank L.

January 1961

By eliminating the body geometry, a comparison is made of the stagnation-point heating which an aero...

Film cooling of small rocket engines

Stechman, Rupert Carl

September 1968

Includes bibliographical references (pages 38-41)An analytical method was developed to predict the t...

Heat-transfer measurements on a blunt spherical-segment nose to a Mach number of 15.1 and flight performance of the rocket-propelled model to a Mach number of 17.8 /

Rumsey, Charles B.
Lee, Dorothy B.
Langley Research Center.

January 1959

"November 1959."Cover title.Includes bibliographical references (p. 17-18).Mode of access: Internet

Heat- and mass-transfer characteristics of an axial-flow liquid-core nuclear rocket employing radiation heat transfer /

Ragsdale, Robert G.
Donovan, Leo F.
Kascak, Albert F.
United States. National Aeronautics and Space Administration.

January 1967

Cover title."August 1967."Includes bibliographical references (p. 31-32).Mode of access: Internet

Dataset of the experimentally measured heat transfer in the throat region of liquid rocket engine thrust chambers

Marco Pizzarelli

August 2021

About 500 experimental heat transfer data taken from the open literature and relevant to the most th...

The use of energy thickness in prediction of throat heat transfer in rocket nozzle

Boldman, D. R.
Graham, R. W.

July 1969

Energy thickness in prediction of throat heat transfer in rocket nozzles using nozzle geometries and...

Estimation of Throat Heat Flux in Liquid Rocket Engines

Pierluigi Concio
Mario Tindaro Migliorino
Francesco Nasuti

January 2019

The problem of prediction of heat flux at throat of liquid rocket engines still constitutes a chall...

Experimental evaluation of heat transfer on a 1030:1 area ratio rocket nozzle /

Kacynski, Kenneth J.
Smith, Tamara A.
Pavli, Albert J.
Lewis Research Center.

January 1987

Prepared at Lewis Research Center."August 1987"--Cover.Includes bibliographical references (p. 24).M...

Theoretical investigation of radiant heat transfer in the fuel region of a gaseous nuclear rocket engine /

Kesten, A. S.
Krascella, N. L.

"January 1967"--cover.Includes bibliographical references.Prepared by United Aircraft Corporation.Mo...

An analysis of thermal radiation heat transfer in a nuclear-rocket nozzle /

Robbins, William H.
United States. National Aeronautics and Space Administration.

Cover title."January 1961."Propulsion systems, nuclear.Includes bibliographical references.Mode of a...

Heat transfer in a 60⁰ half-angle of convergence nozzle with various degrees of roughness /

Reshotko, Meyer.
Ehlers, Robert C.
Boldman, Donald R.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1970

Heat transfer in convergent-divergent nozzles with different values of wall roughness.Includes bibli...

EXPERIMENTAL DETERMINATION OF TEMPERATURE AND PRESSURE GRADIENTS IN ROCKET EXHAUSTS.

Herget, William F.
Levin, B. P.
Suarez-Alfonso, E.

January 1965

Supported by NASA, George C. Marshall Space Flight Center, Huntsville, Alabama.Author Institution: R...

Application of various techniques for determining local heat-transfer coefficients in a rocket engine from transient experimental data /

Liebert, Curt H.
Grant, Ronald W.
Hatch, James E.
Lewis Research Center.

January 1960

"NASA TN D-277.""Lewis Research Center, Cleveland, Ohio.""April 1960."Cover title.Includes bibliogra...

Numerical estimation of nozzle throat heat flux in oxygen-methane rocket engines

Concio, Pierluigi
Tindaro Migliorino, Mario
Bianchi, Daniele
Nasuti, Francesco

January 2022

The prediction of wall heat flux at the nozzle throat is of paramount importance in liquid rocket en...

Numerical approach for the estimation of throat heat flux in liquid rocket engines

Pierluigi Concio
Mario Tindaro Migliorino
Francesco Nasuti

January 2020

The problem of prediction of heat flux at throat of liquid rocket engines still constitutes a challe...

A comparison of stagnation-point heating in a rocket exhaust to that of actual flight /

Paris, Frank L.

January 1961

By eliminating the body geometry, a comparison is made of the stagnation-point heating which an aero...

Film cooling of small rocket engines

Stechman, Rupert Carl

September 1968

Includes bibliographical references (pages 38-41)An analytical method was developed to predict the t...

Heat-transfer measurements on a blunt spherical-segment nose to a Mach number of 15.1 and flight performance of the rocket-propelled model to a Mach number of 17.8 /

Rumsey, Charles B.
Lee, Dorothy B.
Langley Research Center.

January 1959

"November 1959."Cover title.Includes bibliographical references (p. 17-18).Mode of access: Internet

Heat- and mass-transfer characteristics of an axial-flow liquid-core nuclear rocket employing radiation heat transfer /

Ragsdale, Robert G.
Donovan, Leo F.
Kascak, Albert F.
United States. National Aeronautics and Space Administration.

January 1967

Cover title."August 1967."Includes bibliographical references (p. 31-32).Mode of access: Internet

Dataset of the experimentally measured heat transfer in the throat region of liquid rocket engine thrust chambers

Marco Pizzarelli

August 2021

About 500 experimental heat transfer data taken from the open literature and relevant to the most th...

The use of energy thickness in prediction of throat heat transfer in rocket nozzles /

Abstract

Extracted data

The use of energy thickness in prediction of throat heat transfer in rocket nozzles /

Abstract

Extracted data

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