Heat-transfer tests of 20-millimeter projectiles at a Mach number of 5 with an analysis by unsteady scaling laws to predict component temperature rises after firing for various free-flight conditions /

Effect of aerodynamic heating on the flutter of a rectangular wing at a mach number of 2 /

Runyan, Harry L.
Jones, Nan H.
Langley Research Center.

Prepared at the Langley Research Center, Langley Research Center.Cover title."June 1960."--Cover.Inc...

Heat-transfer measurements in free flight at Mach numbers up to 14.6 on a flat-faced conical nose with a total angle of 29©� /

Rumsey, Charles B.
Lee, Dorothy B.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1958

"January 24, 1958; Declassified February 8, 1963."Includes bibliographical references (p. 17).Mode o...

Laminar heat-transfer and pressure-distribution studies on a series of reentry nose shapes at a mach number of 19.4 in helium. /

Wagner, Richard D.
Henderson, Arthur, 1922-
Pine, W. Clint.
United States. National Aeronautics and Space Administration.

Cover title."June 1961."Aerodynamics, missiles and space vehicles; Fluid mechanics.Includes bibliogr...

Aerodynamic-heating data obtained from free-flight tests between Mach numbers of 1 and 5 /

Rumsey, Charles B. (Charles Bertrand)
Hopko, Russell N.
Piland, Robert Owens.
Langley Research Center.

Prepared at Langley Research Center."January 1960."Cover title.Includes bibliographical references (...

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

Exploratory heat-transfer measurements at Mach 10 on a 7.5 ̊total-angle cone downstream of a region of air and helium transpiration cooling /

Dunavant, James C.
Everhart, Philip E.
United States. National Aeronautics and Space Administration.
Langley Research Center.

Heat transfer measurements at Mach 10 on total angle cone downstream of air and helium transpiration...

Heat-transfer measurements on a low-fineness-ratio cylinder at a mach number of 10.4 and angles of attack from 0° to 90° /

Everhart, Philip E.
Langley Research Center.

January 1967

"Langley Research Center, Langley Station, Hampton, Va.""NASA TM X-1400."Cover title.Includes biblio...

Measurements of aerodynamic heat transfer and boundary-layer transition on a 10 degree cone in free flight at supersonic mach numbers up to 5.9 /

Rumsey, Charles B.
Lee, Dorothy B.
United States. National Aeronautics and Space Administration.

Cover title."May 1961."Aerodynamics, missiles and space vehicles; Fluid mechanics; Vehicle performan...

Heat-transfer measurements at a Mach number of 2 in the turbulent boundary layer on a flat plate having a stepwise temperature distribution /

Conti, Raul J. (Raul Jorge)
Langley Research Center.

Prepared at Langley Research Center."November 1959."Cover title.Includes bibliographical references ...

Experimental investigation of base heating and rocket hinge moments for a simulated missile through a Mach number range of 0.8 to 2.0 /

Chiccine, Bruce G.
Shinn, Arthur M.
Valerino, Alfred S.
Langley Research Center.

January 1959

"October 1959."Cover title.Includes bibliographical references (p. 11-12).Mode of access: Internet

An investigation of heat transfer within regions of separated flow at a Mach number of 6.0 /

Holloway, Paul F.
Creekmore, Helen S.
Sterrett, James R.
Langley Research Center.

Prepared at Langley Research Center."November 1965"--Cover.Includes bibliographical references (p. 3...

Experimental and theoretical study of heat conduction for air up to 5000 degrees F /

Peng, Tzy-Cheng.
Ahtye, Warren F.
United States. National Aeronautics and Space Administration.

Cover title."February 1961."Aerodynamics, missiles and space vehicles; Chemical engineering; Chemist...

Some observations of base heating at Mach 3.0 on a simulated missile with JP-4 liquid-oxygen rocket /

Samanich, Nick E.
Barnett, Donald D.
Lovell, J. Calvin.
Lewis Research Center.

January 1960

"November 1960."Cover title.Includes bibliographical references (p. 8).Mode of access: Internet

Measurements of aerodynamic heat transfer on a 15 degree cone-cylinder-flare configuration in free flight at mach numbers up to 4.7 /

Rumsey, Charles R.
Lee, Dorothy B.
United States. National Aeronautics and Space Administration.

Cover title."May 1961."Aerodynamics, aircraft; Aerodynamics, missiles and space vehicles; Fluid mech...

Experimental and predicted heating distributions for biconics at incidence in air at Mach 10 /

Miller, Charles G. (Charles George), 1940-
Langley Research Center.

January 1984

Prepared at Langley Research Center."November 1984"--Cover.Includes bibliographical references (p. 1...

Effect of aerodynamic heating on the flutter of a rectangular wing at a mach number of 2 /

Runyan, Harry L.
Jones, Nan H.
Langley Research Center.

Prepared at the Langley Research Center, Langley Research Center.Cover title."June 1960."--Cover.Inc...

Heat-transfer measurements in free flight at Mach numbers up to 14.6 on a flat-faced conical nose with a total angle of 29©� /

Rumsey, Charles B.
Lee, Dorothy B.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1958

"January 24, 1958; Declassified February 8, 1963."Includes bibliographical references (p. 17).Mode o...

Laminar heat-transfer and pressure-distribution studies on a series of reentry nose shapes at a mach number of 19.4 in helium. /

Wagner, Richard D.
Henderson, Arthur, 1922-
Pine, W. Clint.
United States. National Aeronautics and Space Administration.

Cover title."June 1961."Aerodynamics, missiles and space vehicles; Fluid mechanics.Includes bibliogr...

Aerodynamic-heating data obtained from free-flight tests between Mach numbers of 1 and 5 /

Rumsey, Charles B. (Charles Bertrand)
Hopko, Russell N.
Piland, Robert Owens.
Langley Research Center.

Prepared at Langley Research Center."January 1960."Cover title.Includes bibliographical references (...

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

Exploratory heat-transfer measurements at Mach 10 on a 7.5 ̊total-angle cone downstream of a region of air and helium transpiration cooling /

Dunavant, James C.
Everhart, Philip E.
United States. National Aeronautics and Space Administration.
Langley Research Center.

Heat transfer measurements at Mach 10 on total angle cone downstream of air and helium transpiration...

Heat-transfer measurements on a low-fineness-ratio cylinder at a mach number of 10.4 and angles of attack from 0° to 90° /

Everhart, Philip E.
Langley Research Center.

January 1967

"Langley Research Center, Langley Station, Hampton, Va.""NASA TM X-1400."Cover title.Includes biblio...

Measurements of aerodynamic heat transfer and boundary-layer transition on a 10 degree cone in free flight at supersonic mach numbers up to 5.9 /

Rumsey, Charles B.
Lee, Dorothy B.
United States. National Aeronautics and Space Administration.

Cover title."May 1961."Aerodynamics, missiles and space vehicles; Fluid mechanics; Vehicle performan...

Heat-transfer measurements at a Mach number of 2 in the turbulent boundary layer on a flat plate having a stepwise temperature distribution /

Conti, Raul J. (Raul Jorge)
Langley Research Center.

Prepared at Langley Research Center."November 1959."Cover title.Includes bibliographical references ...

Experimental investigation of base heating and rocket hinge moments for a simulated missile through a Mach number range of 0.8 to 2.0 /

Chiccine, Bruce G.
Shinn, Arthur M.
Valerino, Alfred S.
Langley Research Center.

January 1959

"October 1959."Cover title.Includes bibliographical references (p. 11-12).Mode of access: Internet

An investigation of heat transfer within regions of separated flow at a Mach number of 6.0 /

Holloway, Paul F.
Creekmore, Helen S.
Sterrett, James R.
Langley Research Center.

Prepared at Langley Research Center."November 1965"--Cover.Includes bibliographical references (p. 3...

Experimental and theoretical study of heat conduction for air up to 5000 degrees F /

Peng, Tzy-Cheng.
Ahtye, Warren F.
United States. National Aeronautics and Space Administration.

Cover title."February 1961."Aerodynamics, missiles and space vehicles; Chemical engineering; Chemist...

Some observations of base heating at Mach 3.0 on a simulated missile with JP-4 liquid-oxygen rocket /

Samanich, Nick E.
Barnett, Donald D.
Lovell, J. Calvin.
Lewis Research Center.

January 1960

"November 1960."Cover title.Includes bibliographical references (p. 8).Mode of access: Internet

Measurements of aerodynamic heat transfer on a 15 degree cone-cylinder-flare configuration in free flight at mach numbers up to 4.7 /

Rumsey, Charles R.
Lee, Dorothy B.
United States. National Aeronautics and Space Administration.

Cover title."May 1961."Aerodynamics, aircraft; Aerodynamics, missiles and space vehicles; Fluid mech...

Experimental and predicted heating distributions for biconics at incidence in air at Mach 10 /

Miller, Charles G. (Charles George), 1940-
Langley Research Center.

January 1984

Prepared at Langley Research Center."November 1984"--Cover.Includes bibliographical references (p. 1...

Effect of aerodynamic heating on the flutter of a rectangular wing at a mach number of 2 /

Runyan, Harry L.
Jones, Nan H.
Langley Research Center.

Prepared at the Langley Research Center, Langley Research Center.Cover title."June 1960."--Cover.Inc...

Heat-transfer measurements in free flight at Mach numbers up to 14.6 on a flat-faced conical nose with a total angle of 29©� /

Rumsey, Charles B.
Lee, Dorothy B.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1958

"January 24, 1958; Declassified February 8, 1963."Includes bibliographical references (p. 17).Mode o...

Laminar heat-transfer and pressure-distribution studies on a series of reentry nose shapes at a mach number of 19.4 in helium. /

Wagner, Richard D.
Henderson, Arthur, 1922-
Pine, W. Clint.
United States. National Aeronautics and Space Administration.

Cover title."June 1961."Aerodynamics, missiles and space vehicles; Fluid mechanics.Includes bibliogr...

Heat-transfer tests of 20-millimeter projectiles at a Mach number of 5 with an analysis by unsteady scaling laws to predict component temperature rises after firing for various free-flight conditions /

Abstract

Extracted data

Heat-transfer tests of 20-millimeter projectiles at a Mach number of 5 with an analysis by unsteady scaling laws to predict component temperature rises after firing for various free-flight conditions /

Abstract

Extracted data

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