Mach 6 experimental and theoretical stability and performance of a cruciform missile at angles of attack up to 65⁰ /

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

Flight test performance and description of a rocket vehicle for producing low-speed artificial meteors /

Brown, Clarence A.
Keating, Jean C.
Langley Research Center.

Prepared at Langley Research Center."April 1964"--Cover.Includes bibliographical references (p. 9).M...

Dynamic response of a forward-swept-wing model at angles of attack up to 15 at a Mach number of 0.8 /

Doggett, Robert V.
Ricketts, Rodney H.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1980

Nov. 1980."Langley Research Center."Includes bibliographical references.Mode of access: Internet

Mach 6 flow field surveys beneath the forebody of an airbreatinng missile /

Johnston, Patrick J.
Hunt, James L. (James Larry), 1939-
Langley Research Center.

January 1986

Prepared at Langley Research Center."March 1986"--Cover.Includes bibliographical references (p. 151-...

Stability and control characteristics of a three-surface advanced fighter configuration at angles of attack up to 45?/

Henderson, William P.
Leavitt, Laurence D.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

"September 1981"--Cover."Langley Research Center."Includes bibliographical references.Mode of access...

Stability and control characteristics of a monoplanar missile configuration with triform-tail-fin arrangements at mach numbers from 1.70 to 2.86 /

Lamb, Milton.
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."Bibliography: p. 10.Mode of acc...

Stability and control characteristics at Mach numbers from 0.20 to 4.63 of a cruciform air-to-air missile with triangular canard controls and a trapezoidal wing /

Graves, Ernald B.
Fournier, Roger H.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Errata sheet inserted.Chiefly graphs.Cover title.Mode of access:...

Langley 9-inch supersonic tunnel tests of several modifications of a supersonic missile having tandem cruciform lifting surfaces : three-component data results of models having ratios of wing span to tail span less than 1 /

Rainey, Robert W.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1960

"March 7, 1951; Declassified July 28, 1960."Includes bibliographical references (p. 7).Mode of acces...

Static longitudinal stability and control characteristics at a mach number of 2.01 of a hypersonic missile configuration having all-movable wing and tail surfaces /

Robinson, Ross B.
Foster, Gerald V.
Langley Research Center.

January 1961

"April 1961."Cover title.Includes bibliographical references (p. 6).Mode of access: Internet

Stability and control characteristics of an air-breathing missile configuration having a forward located inlet /

Sawyer, Wallace C.
Hayes, Clyde.
Langley Research Center.

January 1976

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 9).Mode of a...

Subsonic longitudinal and lateral-directional characteristics of a forward-swept-wing fighter configuration at angles of attack up to 47⁰ /

Mann, Michael J.
Fox, Charles H.
Huffman, Jarrett K.
Langley Research Center.

January 1987

Prepared at Langley Research Center."September 1987"--Cover.Includes bibliographical references (p. ...

Longitudinal stability and control characteristics from a flight investigation of a cruciform canard missile configuration having an exposed wing-canard area ratio of 16:1 /

Moul, Martin T.
Wineman, Andrew R.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1952

"June 25, 1952."Includes bibliographical references (p. 14).Mode of access: Internet

Static stability investigation of a sounding-rocket vehicle at Mach numbers from 1.50 to 4.63 /

Babb, C. Donald.
Fuller, Dennis E.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1967

Cover title."June 1967."Includes bibliographical references (p. 7).Mode of access: Internet

Experimental stability and control results at Mach 19 of an entry vehicle designed for an intermediate lift-drag ratio /

Johnston, Patrick J.
Witcofski, Robert D.
Langley Research Center.

Prepared at Langley Research Center."February 1968"--Cover.Includes bibliographical references (p. 1...

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...

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

Flight test performance and description of a rocket vehicle for producing low-speed artificial meteors /

Brown, Clarence A.
Keating, Jean C.
Langley Research Center.

Prepared at Langley Research Center."April 1964"--Cover.Includes bibliographical references (p. 9).M...

Dynamic response of a forward-swept-wing model at angles of attack up to 15 at a Mach number of 0.8 /

Doggett, Robert V.
Ricketts, Rodney H.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1980

Nov. 1980."Langley Research Center."Includes bibliographical references.Mode of access: Internet

Mach 6 flow field surveys beneath the forebody of an airbreatinng missile /

Johnston, Patrick J.
Hunt, James L. (James Larry), 1939-
Langley Research Center.

January 1986

Prepared at Langley Research Center."March 1986"--Cover.Includes bibliographical references (p. 151-...

Stability and control characteristics of a three-surface advanced fighter configuration at angles of attack up to 45?/

Henderson, William P.
Leavitt, Laurence D.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

"September 1981"--Cover."Langley Research Center."Includes bibliographical references.Mode of access...

Stability and control characteristics of a monoplanar missile configuration with triform-tail-fin arrangements at mach numbers from 1.70 to 2.86 /

Lamb, Milton.
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."Bibliography: p. 10.Mode of acc...

Stability and control characteristics at Mach numbers from 0.20 to 4.63 of a cruciform air-to-air missile with triangular canard controls and a trapezoidal wing /

Graves, Ernald B.
Fournier, Roger H.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Errata sheet inserted.Chiefly graphs.Cover title.Mode of access:...

Langley 9-inch supersonic tunnel tests of several modifications of a supersonic missile having tandem cruciform lifting surfaces : three-component data results of models having ratios of wing span to tail span less than 1 /

Rainey, Robert W.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1960

"March 7, 1951; Declassified July 28, 1960."Includes bibliographical references (p. 7).Mode of acces...

Static longitudinal stability and control characteristics at a mach number of 2.01 of a hypersonic missile configuration having all-movable wing and tail surfaces /

Robinson, Ross B.
Foster, Gerald V.
Langley Research Center.

January 1961

"April 1961."Cover title.Includes bibliographical references (p. 6).Mode of access: Internet

Stability and control characteristics of an air-breathing missile configuration having a forward located inlet /

Sawyer, Wallace C.
Hayes, Clyde.
Langley Research Center.

January 1976

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 9).Mode of a...

Subsonic longitudinal and lateral-directional characteristics of a forward-swept-wing fighter configuration at angles of attack up to 47⁰ /

Mann, Michael J.
Fox, Charles H.
Huffman, Jarrett K.
Langley Research Center.

January 1987

Prepared at Langley Research Center."September 1987"--Cover.Includes bibliographical references (p. ...

Longitudinal stability and control characteristics from a flight investigation of a cruciform canard missile configuration having an exposed wing-canard area ratio of 16:1 /

Moul, Martin T.
Wineman, Andrew R.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1952

"June 25, 1952."Includes bibliographical references (p. 14).Mode of access: Internet

Static stability investigation of a sounding-rocket vehicle at Mach numbers from 1.50 to 4.63 /

Babb, C. Donald.
Fuller, Dennis E.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1967

Cover title."June 1967."Includes bibliographical references (p. 7).Mode of access: Internet

Experimental stability and control results at Mach 19 of an entry vehicle designed for an intermediate lift-drag ratio /

Johnston, Patrick J.
Witcofski, Robert D.
Langley Research Center.

Prepared at Langley Research Center."February 1968"--Cover.Includes bibliographical references (p. 1...

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...

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

Flight test performance and description of a rocket vehicle for producing low-speed artificial meteors /

Brown, Clarence A.
Keating, Jean C.
Langley Research Center.

Prepared at Langley Research Center."April 1964"--Cover.Includes bibliographical references (p. 9).M...

Dynamic response of a forward-swept-wing model at angles of attack up to 15 at a Mach number of 0.8 /

Doggett, Robert V.
Ricketts, Rodney H.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1980

Nov. 1980."Langley Research Center."Includes bibliographical references.Mode of access: Internet

Mach 6 experimental and theoretical stability and performance of a cruciform missile at angles of attack up to 65⁰ /

Abstract

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Mach 6 experimental and theoretical stability and performance of a cruciform missile at angles of attack up to 65⁰ /

Abstract

Extracted data

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