Charts for equilibrium isentropic expansion of air behind shocks up to 50,000 per second (15.24 kilometers per second) /

Pressure distributions and shock shapes for 12.84/̊7 ̊on-axis and bent-nose biconics in air at mach 6 /

Miller, Charles G. (Charles George), 1940-
Gnoffo, Peter A.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

Subject category 02."December 1981"--Cover."Langley Research Center."Mode of access: Internet

Flight measurements of surface pressures on a flexible supercritical research wing /

Eckstrom, Clinton V.
Langley Research Center.

January 1985

Prepared at Langley Research Center."December 1985"--Cover.Includes bibliographical references (p. 1...

Comparisons of two-dimensional shock-expansion theory with experimental aerodynamic data for delta-planform wings at high supersonic speeds /

Jernell, Lloyd S.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 10).Mode of ...

Charts for equilibrium flow properties of air in hypervelocity nozzles /

Jorgensen, Leland H.
Baum, Geyle M.
Ames Research Center.

Prepared at Ames Research Center."September 1962."Cover title.Includes bibliographical references (p...

A study of equilibrium real-gas effects in hypersonic air nozzles, including charts of thermodynamic properties for equilibrium air /

Erickson, Wayne D. (Wayne Douglas), 1932-
Creekmore, Helen S.
Langley Research Center.

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

Preliminary analysis of a simulated meteor reentry at 9.8 kilometers per second /

Jewell, W. O.
Wineman, Andrew Rugh, 1924-
Langley Research Center.

Prepared at Langley Research Center."April 1964"--Cover.Includes bibliographical references (p. 11)....

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 (...

Program and charts for determining shock tube, expansion tube, and expansion tunnel flow quantities for real air /

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

January 1975

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 103-104).Mod...

Charts for air flow properties in equilibrium and frozen flows in hypervelocity nozzles /

Yoshikawa, Kenneth K.
Katzen, Elliott D.
United States. National Aeronautics and Space Administration.

Cover title."April 1961."Aerodynamics, missiles and space vehicles; Fluid mechanics; Propulsion syst...

Transition fixing for hypersonic flow /

Sterrett, James R.
Langley Research Center.

Prepared at Langley Research Center."October 1967"--Cover.Includes bibliographical references (p. 12...

Charts for determing potential minimum sonic-boom overpressures for supersonic cruise aircraft /

Darden, Christine M.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

"Langley Research Center.""March 1981"--Cover.Includes bibliographical references.Mode of access: In...

A semiempirical collision model for plasmas /

Meador, Willard E.
United States. National Aeronautics and Space Administration.
Langley Research Center.

Prepared at Langley Research Center."May 1969"--Cover.Includes bibliographical references (p. 32).Mo...

Pressure distributions on blunt-delta wings at angles of attack up to 90 degrees and Mach number of 6.85 /

Bernot, Peter T.
United States. National Aeronautics and Space Administration.

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

Pressure and force data for a flat wing and a warped conical wing having a shockless recompression at Mach 1.62 /

Miller, David S.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Langley Research Center.

January 1981

"April 1981"--Cover."Langley Research Center."Includes bibliographical references.Mode of access: In...

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

Pressure distributions and shock shapes for 12.84/̊7 ̊on-axis and bent-nose biconics in air at mach 6 /

Miller, Charles G. (Charles George), 1940-
Gnoffo, Peter A.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

Subject category 02."December 1981"--Cover."Langley Research Center."Mode of access: Internet

Flight measurements of surface pressures on a flexible supercritical research wing /

Eckstrom, Clinton V.
Langley Research Center.

January 1985

Prepared at Langley Research Center."December 1985"--Cover.Includes bibliographical references (p. 1...

Comparisons of two-dimensional shock-expansion theory with experimental aerodynamic data for delta-planform wings at high supersonic speeds /

Jernell, Lloyd S.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 10).Mode of ...

Charts for equilibrium flow properties of air in hypervelocity nozzles /

Jorgensen, Leland H.
Baum, Geyle M.
Ames Research Center.

Prepared at Ames Research Center."September 1962."Cover title.Includes bibliographical references (p...

A study of equilibrium real-gas effects in hypersonic air nozzles, including charts of thermodynamic properties for equilibrium air /

Erickson, Wayne D. (Wayne Douglas), 1932-
Creekmore, Helen S.
Langley Research Center.

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

Preliminary analysis of a simulated meteor reentry at 9.8 kilometers per second /

Jewell, W. O.
Wineman, Andrew Rugh, 1924-
Langley Research Center.

Prepared at Langley Research Center."April 1964"--Cover.Includes bibliographical references (p. 11)....

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 (...

Program and charts for determining shock tube, expansion tube, and expansion tunnel flow quantities for real air /

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

January 1975

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 103-104).Mod...

Charts for air flow properties in equilibrium and frozen flows in hypervelocity nozzles /

Yoshikawa, Kenneth K.
Katzen, Elliott D.
United States. National Aeronautics and Space Administration.

Cover title."April 1961."Aerodynamics, missiles and space vehicles; Fluid mechanics; Propulsion syst...

Transition fixing for hypersonic flow /

Sterrett, James R.
Langley Research Center.

Prepared at Langley Research Center."October 1967"--Cover.Includes bibliographical references (p. 12...

Charts for determing potential minimum sonic-boom overpressures for supersonic cruise aircraft /

Darden, Christine M.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

"Langley Research Center.""March 1981"--Cover.Includes bibliographical references.Mode of access: In...

A semiempirical collision model for plasmas /

Meador, Willard E.
United States. National Aeronautics and Space Administration.
Langley Research Center.

Prepared at Langley Research Center."May 1969"--Cover.Includes bibliographical references (p. 32).Mo...

Pressure distributions on blunt-delta wings at angles of attack up to 90 degrees and Mach number of 6.85 /

Bernot, Peter T.
United States. National Aeronautics and Space Administration.

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

Pressure and force data for a flat wing and a warped conical wing having a shockless recompression at Mach 1.62 /

Miller, David S.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Langley Research Center.

January 1981

"April 1981"--Cover."Langley Research Center."Includes bibliographical references.Mode of access: In...

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

Pressure distributions and shock shapes for 12.84/̊7 ̊on-axis and bent-nose biconics in air at mach 6 /

Miller, Charles G. (Charles George), 1940-
Gnoffo, Peter A.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

Subject category 02."December 1981"--Cover."Langley Research Center."Mode of access: Internet

Flight measurements of surface pressures on a flexible supercritical research wing /

Eckstrom, Clinton V.
Langley Research Center.

January 1985

Prepared at Langley Research Center."December 1985"--Cover.Includes bibliographical references (p. 1...

Comparisons of two-dimensional shock-expansion theory with experimental aerodynamic data for delta-planform wings at high supersonic speeds /

Jernell, Lloyd S.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 10).Mode of ...

Charts for equilibrium isentropic expansion of air behind shocks up to 50,000 per second (15.24 kilometers per second) /

Abstract

Extracted data

Charts for equilibrium isentropic expansion of air behind shocks up to 50,000 per second (15.24 kilometers per second) /

Abstract

Extracted data

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