Ground measurements of the shock-wave noise from supersonic bomber airplanes in the altitude range from 30,000 to 50,000 feet. /

Random deviations from cruise altitudes of a turbojet transport transport at altitudes between 20,000 and 41,000 feet. /

Gracey, William
Shipp, Jo Ann.
United States. National Aeronautics and Space Administration.

Cover title."April 1961."Aircraft; Aircraft safety and noise; Piloting; Vehicle Performance.Includes...

An investigation of landing-contact conditions for a large turbojet transport during routine daylight operations /

Stickle, Joseph W.
Silsby, Norman S.
United States. National Aeronautics and Space Administration.

Cover title."October 1960."Aircraft safety and noise; Structures; Vehicle performance.Includes bibli...

A brief evaluation of helisopter wake as a potential operational hazard to aircraft /

Connor, Andrew B.
O'Bryan, Thomas C.
United States. National Aeronautics and Space Administration.

Cover title."March 1962."Aircraft safety and noise.Includes bibliographical references.Mode of acces...

Ground measurements of airplane shock-wave noise at Mach numbers to 2.0 and at altitudes to 60,000 feet /

Lina, Lindsay J.
Maglieri, Domenic J.
Langley Research Center.

January 1960

"NASA TN D-235.""Langley Research Center, Langley Field, Va.""March 1960."Cover title.Includes bibli...

Lateral-spread sonic-boom ground-pressure measurements from airplanes at altitudes to 75,000 feet and at Mach numbers to 2.0 /

Maglieri, Domenic J.
United States. National Aeronautics and Space Administration.
Langley Research Center.

"November 1963."Cover title.Includes bibliographical references.Mode of access: Internet

Ground and in-flight acoustic and performance characteristics of jet-aircraft exhaust noise supressors /

Coles, Willard D.
Swann, William H.
Mihaloew, John A,
United States. National Aeronautics and Space Administration.

Cover title."August 1961."Aerodynamics, aircraft; Aircraft; Aircraft safety and noise; Propulsion sy...

An investigation of the influence of lift on sonic-boom intensity by means of wind-tunnel measurements of the pressure fields of several wing-body combinations at a mach number of 2.01 /

Carlson, Harry W.
United States. National Aeronautics and Space Administration.

Cover title."July 1961."Aerodynamics, aircraft; Aerodynamics, missiles and space vehicles; Aircraft ...

Survey of altitude-measuring methods for the vertical separation of aircraft /

Gracey, William
United States. National Aeronautics and Space Administration.

Cover title."March 1961."Aircraft; Aircraft safety and noise.Includes bibliographical references.Mod...

Aerodynamic characteristics of parachutes at mach numbers from 1.6 to 3 /

Maynard, Julian D.
United States. National Aeronautics and Space Administration.

Cover title."May 1961."Aircraft safety and noise.Includes bibliographical references.Mode of access:...

Noise considerations in the design and operation of V/STOL aircraft /

Maglieri, Domenic J.
Hubbard, Harvey H.
Hilton, David A.
United States. National Aeronautics and Space Administration.

Cover title."April 1961."Aircraft; Aircraft safety and noise.Includes bibliographical references.Mod...

Experimental and calculated flow fields produced by airplanes flying at supersonic speeds /

Smith, Harriet J.
United States. National Aeronautics and Space Administration.

Cover title."November 1960."Aerodynamics aircraft; Aircraft safety and noise.Includes bibliographica...

An investigation of some aspects of the sonic boom by means of wind-tunnel measurements of pressures about several bodies at a mach number of 2.01 /

Carlson, Harry W.
United States. National Aeronautics and Space Administration.

Cover title."December 1959."Aerodynamics, fundamental; Bodies; Noise.Includes bibliographical refere...

Transonic performance characteristics of several jet noise suppressors /

Schmeer, James W.
Cassetti, Marlowe D.
Salters, Leland B.
United States. National Aeronautics and Space Administration.

Cover title."July 1960."Aircraft; Aircraft safety and noise; Propulsion system elements.Includes bib...

Measurements of sonic booms generated by an airplane flying at Mach 3.5 and 4.8 /

Green, Karen S.
Putnam, Terrill W.
Flight Research Center (U.S.)

January 1974

Prepared at NASA Flight Research Center.Cover title.Includes bibliographical references (p. 8).Mode ...

A wind-tunnel investigation at a Mach number of 2.01 of the sonic-boom characteristics of three wing-body combinations differing in wing longitudinal location /

Morris, Odell A.
United States. National Aeronautics and Space Administration.

Cover title."September 1962."Aerodynamics, aircraft; Aircraft; Aircraft safety and noise.Includes bi...

Random deviations from cruise altitudes of a turbojet transport transport at altitudes between 20,000 and 41,000 feet. /

Gracey, William
Shipp, Jo Ann.
United States. National Aeronautics and Space Administration.

Cover title."April 1961."Aircraft; Aircraft safety and noise; Piloting; Vehicle Performance.Includes...

An investigation of landing-contact conditions for a large turbojet transport during routine daylight operations /

Stickle, Joseph W.
Silsby, Norman S.
United States. National Aeronautics and Space Administration.

Cover title."October 1960."Aircraft safety and noise; Structures; Vehicle performance.Includes bibli...

A brief evaluation of helisopter wake as a potential operational hazard to aircraft /

Connor, Andrew B.
O'Bryan, Thomas C.
United States. National Aeronautics and Space Administration.

Cover title."March 1962."Aircraft safety and noise.Includes bibliographical references.Mode of acces...

Ground measurements of airplane shock-wave noise at Mach numbers to 2.0 and at altitudes to 60,000 feet /

Lina, Lindsay J.
Maglieri, Domenic J.
Langley Research Center.

January 1960

"NASA TN D-235.""Langley Research Center, Langley Field, Va.""March 1960."Cover title.Includes bibli...

Lateral-spread sonic-boom ground-pressure measurements from airplanes at altitudes to 75,000 feet and at Mach numbers to 2.0 /

Maglieri, Domenic J.
United States. National Aeronautics and Space Administration.
Langley Research Center.

"November 1963."Cover title.Includes bibliographical references.Mode of access: Internet

Ground and in-flight acoustic and performance characteristics of jet-aircraft exhaust noise supressors /

Coles, Willard D.
Swann, William H.
Mihaloew, John A,
United States. National Aeronautics and Space Administration.

Cover title."August 1961."Aerodynamics, aircraft; Aircraft; Aircraft safety and noise; Propulsion sy...

An investigation of the influence of lift on sonic-boom intensity by means of wind-tunnel measurements of the pressure fields of several wing-body combinations at a mach number of 2.01 /

Carlson, Harry W.
United States. National Aeronautics and Space Administration.

Cover title."July 1961."Aerodynamics, aircraft; Aerodynamics, missiles and space vehicles; Aircraft ...

Survey of altitude-measuring methods for the vertical separation of aircraft /

Gracey, William
United States. National Aeronautics and Space Administration.

Cover title."March 1961."Aircraft; Aircraft safety and noise.Includes bibliographical references.Mod...

Aerodynamic characteristics of parachutes at mach numbers from 1.6 to 3 /

Maynard, Julian D.
United States. National Aeronautics and Space Administration.

Cover title."May 1961."Aircraft safety and noise.Includes bibliographical references.Mode of access:...

Noise considerations in the design and operation of V/STOL aircraft /

Maglieri, Domenic J.
Hubbard, Harvey H.
Hilton, David A.
United States. National Aeronautics and Space Administration.

Cover title."April 1961."Aircraft; Aircraft safety and noise.Includes bibliographical references.Mod...

Experimental and calculated flow fields produced by airplanes flying at supersonic speeds /

Smith, Harriet J.
United States. National Aeronautics and Space Administration.

Cover title."November 1960."Aerodynamics aircraft; Aircraft safety and noise.Includes bibliographica...

An investigation of some aspects of the sonic boom by means of wind-tunnel measurements of pressures about several bodies at a mach number of 2.01 /

Carlson, Harry W.
United States. National Aeronautics and Space Administration.

Cover title."December 1959."Aerodynamics, fundamental; Bodies; Noise.Includes bibliographical refere...

Transonic performance characteristics of several jet noise suppressors /

Schmeer, James W.
Cassetti, Marlowe D.
Salters, Leland B.
United States. National Aeronautics and Space Administration.

Cover title."July 1960."Aircraft; Aircraft safety and noise; Propulsion system elements.Includes bib...

Measurements of sonic booms generated by an airplane flying at Mach 3.5 and 4.8 /

Green, Karen S.
Putnam, Terrill W.
Flight Research Center (U.S.)

January 1974

Prepared at NASA Flight Research Center.Cover title.Includes bibliographical references (p. 8).Mode ...

A wind-tunnel investigation at a Mach number of 2.01 of the sonic-boom characteristics of three wing-body combinations differing in wing longitudinal location /

Morris, Odell A.
United States. National Aeronautics and Space Administration.

Cover title."September 1962."Aerodynamics, aircraft; Aircraft; Aircraft safety and noise.Includes bi...

Random deviations from cruise altitudes of a turbojet transport transport at altitudes between 20,000 and 41,000 feet. /

Gracey, William
Shipp, Jo Ann.
United States. National Aeronautics and Space Administration.

Cover title."April 1961."Aircraft; Aircraft safety and noise; Piloting; Vehicle Performance.Includes...

An investigation of landing-contact conditions for a large turbojet transport during routine daylight operations /

Stickle, Joseph W.
Silsby, Norman S.
United States. National Aeronautics and Space Administration.

Cover title."October 1960."Aircraft safety and noise; Structures; Vehicle performance.Includes bibli...

A brief evaluation of helisopter wake as a potential operational hazard to aircraft /

Connor, Andrew B.
O'Bryan, Thomas C.
United States. National Aeronautics and Space Administration.

Cover title."March 1962."Aircraft safety and noise.Includes bibliographical references.Mode of acces...

Ground measurements of the shock-wave noise from supersonic bomber airplanes in the altitude range from 30,000 to 50,000 feet. /

Abstract

Extracted data

Ground measurements of the shock-wave noise from supersonic bomber airplanes in the altitude range from 30,000 to 50,000 feet. /

Abstract

Extracted data

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