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

Supersonic investigation of nozzle hinge moments of a modified Saturn C-1 model with and without jet flow /

Charczenko, Nickolai.
Lowery, Jerry L.
Langley Research Center.

Prepared at Langley Research Center."November 1963"--Cover.Includes bibliographical references (p. 9...

Sideslip characteristics at various angles of attack for several hypersonic missile configurations with canard controls at a mach number of 2.01 /

Foster, Gerald V.
Langley Research Center.

January 1959

"November 1959"--Cover.Caption title.Includes bibliographical references (p. 6).Mode of access: Inte...

Experimental study of aeroelastic instability of overexpanded rocket nozzle extensions /

Tuovila, W. J. (Weimer J.)
Land, Norman S.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1968

Cover title."April 1968."Includes bibliographical references (p. 6).Mode of access: Internet

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

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

Experimental investigation of two-stage air-cooled turbine suitable for flight at Mach 2.5 /

Schum, Harold J.
Nunamaker, Robert R.
Petrash, Donald A.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1959

"November 1959."Cover title.Includes bibliographical references (p. 27).Mode of access: Internet

Preliminary investigation of the effects of several seeker-nose configurations on the longitudinal characteristics of a canard-type missile at a Mach number of 1.60 /

Robins, A. Warner.

"October 30, 1953. Declassified September 17, 1958"--Cover.Caption title.Includes bibliographical re...

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...

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 (...

Aerodynamic heating tests of missile stabilizers in a free jet at Mach number 2 /

Vosteen, Louis F.
Langley Research Center.

January 1960

"Declassified February 8, 1963.""September 1960."Cover title.Includes bibliographical references (p....

Heat-transfer and pressure measurements on a concove-nose cylinder for a mach number range of 2.49 to 4.44 /

Stallings, Jr., Robert L.
Burbank, Paige B.
Langley Research Center.

January 1959

"October 1959"--Cover.Caption title.Includes bibliographical references (p. 10).Mode of access: Inte...

Static stability investigation of a single-stage sounding rocket at Mach numbers from 0.60 to 1.20 /

Ferris, James C.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1967

Cover title."June 1967."Includes bibliographical references (p. 8).Mode of access: Internet

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 /

Trimpi, Robert L.
Jones, Robert A.
Gallagher, James G.
Langley Research Center.

Prepared at Langley Research Center."May 1961."Cover title.Includes bibliographical references (p. 1...

Jet effects at supersonic speeds on base and afterbody pressures of a missile model having single and multiple jets /

Charczenko, Nickolai.
Hayes, Clyde.
Langley Research Center.

Prepared at Langley Research Center."November 1963"--Cover.Includes bibliographical references (p. 8...

Effects of simulated rocket-jet exhaust on stability and control of a research-type airplane configuration at mach number of 6.86 /

Fetterman, David E.
United States. National Aeronautics and Space Administration.

"October 1959."Cover title.Includes bibliographical references (p. 15).Mode of access: Internet

Supersonic investigation of nozzle hinge moments of a modified Saturn C-1 model with and without jet flow /

Charczenko, Nickolai.
Lowery, Jerry L.
Langley Research Center.

Prepared at Langley Research Center."November 1963"--Cover.Includes bibliographical references (p. 9...

Sideslip characteristics at various angles of attack for several hypersonic missile configurations with canard controls at a mach number of 2.01 /

Foster, Gerald V.
Langley Research Center.

January 1959

"November 1959"--Cover.Caption title.Includes bibliographical references (p. 6).Mode of access: Inte...

Experimental study of aeroelastic instability of overexpanded rocket nozzle extensions /

Tuovila, W. J. (Weimer J.)
Land, Norman S.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1968

Cover title."April 1968."Includes bibliographical references (p. 6).Mode of access: Internet

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

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

Experimental investigation of two-stage air-cooled turbine suitable for flight at Mach 2.5 /

Schum, Harold J.
Nunamaker, Robert R.
Petrash, Donald A.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1959

"November 1959."Cover title.Includes bibliographical references (p. 27).Mode of access: Internet

Preliminary investigation of the effects of several seeker-nose configurations on the longitudinal characteristics of a canard-type missile at a Mach number of 1.60 /

Robins, A. Warner.

"October 30, 1953. Declassified September 17, 1958"--Cover.Caption title.Includes bibliographical re...

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...

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 (...

Aerodynamic heating tests of missile stabilizers in a free jet at Mach number 2 /

Vosteen, Louis F.
Langley Research Center.

January 1960

"Declassified February 8, 1963.""September 1960."Cover title.Includes bibliographical references (p....

Heat-transfer and pressure measurements on a concove-nose cylinder for a mach number range of 2.49 to 4.44 /

Stallings, Jr., Robert L.
Burbank, Paige B.
Langley Research Center.

January 1959

"October 1959"--Cover.Caption title.Includes bibliographical references (p. 10).Mode of access: Inte...

Static stability investigation of a single-stage sounding rocket at Mach numbers from 0.60 to 1.20 /

Ferris, James C.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1967

Cover title."June 1967."Includes bibliographical references (p. 8).Mode of access: Internet

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 /

Trimpi, Robert L.
Jones, Robert A.
Gallagher, James G.
Langley Research Center.

Prepared at Langley Research Center."May 1961."Cover title.Includes bibliographical references (p. 1...

Jet effects at supersonic speeds on base and afterbody pressures of a missile model having single and multiple jets /

Charczenko, Nickolai.
Hayes, Clyde.
Langley Research Center.

Prepared at Langley Research Center."November 1963"--Cover.Includes bibliographical references (p. 8...

Effects of simulated rocket-jet exhaust on stability and control of a research-type airplane configuration at mach number of 6.86 /

Fetterman, David E.
United States. National Aeronautics and Space Administration.

"October 1959."Cover title.Includes bibliographical references (p. 15).Mode of access: Internet

Supersonic investigation of nozzle hinge moments of a modified Saturn C-1 model with and without jet flow /

Charczenko, Nickolai.
Lowery, Jerry L.
Langley Research Center.

Prepared at Langley Research Center."November 1963"--Cover.Includes bibliographical references (p. 9...

Sideslip characteristics at various angles of attack for several hypersonic missile configurations with canard controls at a mach number of 2.01 /

Foster, Gerald V.
Langley Research Center.

January 1959

"November 1959"--Cover.Caption title.Includes bibliographical references (p. 6).Mode of access: Inte...

Experimental study of aeroelastic instability of overexpanded rocket nozzle extensions /

Tuovila, W. J. (Weimer J.)
Land, Norman S.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1968

Cover title."April 1968."Includes bibliographical references (p. 6).Mode of access: Internet

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

Abstract

Extracted data

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

Abstract

Extracted data

Related items

Related items