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

Loads induced on a flat plate at a Mach number of 4.5 with a sonic or supersonic jet exhausting normal to the surface /

Letko, William.
Langley Research Center.

Prepared at Langley Research Center."July 1963."Cover title.Includes bibliographical references (p. ...

Aerodynamic data on large semispan tilting wing with 0.4-diameter chord, single-slotted flap, and single propeller 0.22 chord below wing /

Fink, Marvin P.
United States. National Aeronautics and Space Administration.
Langley Research Center.

January 1969

Prepared at Langley Research Center.N 69-17312.Cover title.Includes bibliographical references (p. 1...

Wind-tunnel results for a modified 17-percent-thick low-speed airfoil section /

McGhee, Robert J.
Beasley, William D.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Langley Research Center.

January 1981

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

Surface pressure data for a supersonic-cruise airplane configuration at mach numbers of 2.30, 2.96, and 3.30 /

Shrout, Barrett L.
Collins, Ida K.
Corlett, William A.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1979

Subject category 02."May 1979"--Cover."Langley Research Center."Includes bibliographical references....

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...

Body-surface pressure data on two monoplane-wing missile configurations with elliptical cross sections at Mach 2.50 /

Allen, Jerry M.
Lamb, Milton.
Hernandez, Gloria.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Langley Research Center.

January 1983

Chiefly tables."Langley Research Center.""September 1983"--Cover.Distributed to depository libraries...

Pressure measurements of the leading edge of a swept wing at Mach 2.2 /

Sorrells, Russell B.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 11).Mode of ...

Wind-tunnel force and flow visualization data at Mach numbers from 1.6 to 4.63 for a series of bodies of revolution at angles of attack from -4 ̊to 60 ̊/

Landrum, Emma Jean.
Babb, C. Donald.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1979

Subject category 02."Langley Research Center.""March 1979"--Cover.Includes bibliographical reference...

Pressure data for four analytically defined arrow wings in supersonic flow /

Townsend, James C. (James Courtland), 1938-
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1980

Sept. 1980."Langley Research Center."Bibliography: p. 16.Mode of access: Internet

Wing-alone aerodynamic characteristics for high angles of attack at supersonic speeds /

Stallings, Robert L.
Lamb, Milton.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

"July 1982"--Cover."Langley Research Center."Includes bibliographical references.Mode of access: Int...

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 (...

Basic pressure measurements on a 0.0667-scale model of the North American X-15 research airplane at transonic speeds /

Osborne, Robert S.
Stafford, Virginia C.
Langley Research Center.
United States. National Aeronautics and Space Administration.

"Langley Research Center, Langely Field, Va.""October 1960."Cover title.Includes bibliographical ref...

Supersonic wings with significant leading-edge thrust at cruise /

Robins, A. Warner.
Mack, Robert J.
Carlson, Harry W.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1982

Subject Category 02."April 1980"--Cover."Langley Research Center."Includes bibliographical reference...

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

Loads induced on a flat plate at a Mach number of 4.5 with a sonic or supersonic jet exhausting normal to the surface /

Letko, William.
Langley Research Center.

Prepared at Langley Research Center."July 1963."Cover title.Includes bibliographical references (p. ...

Aerodynamic data on large semispan tilting wing with 0.4-diameter chord, single-slotted flap, and single propeller 0.22 chord below wing /

Fink, Marvin P.
United States. National Aeronautics and Space Administration.
Langley Research Center.

January 1969

Prepared at Langley Research Center.N 69-17312.Cover title.Includes bibliographical references (p. 1...

Wind-tunnel results for a modified 17-percent-thick low-speed airfoil section /

McGhee, Robert J.
Beasley, William D.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Langley Research Center.

January 1981

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

Surface pressure data for a supersonic-cruise airplane configuration at mach numbers of 2.30, 2.96, and 3.30 /

Shrout, Barrett L.
Collins, Ida K.
Corlett, William A.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1979

Subject category 02."May 1979"--Cover."Langley Research Center."Includes bibliographical references....

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...

Body-surface pressure data on two monoplane-wing missile configurations with elliptical cross sections at Mach 2.50 /

Allen, Jerry M.
Lamb, Milton.
Hernandez, Gloria.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Langley Research Center.

January 1983

Chiefly tables."Langley Research Center.""September 1983"--Cover.Distributed to depository libraries...

Pressure measurements of the leading edge of a swept wing at Mach 2.2 /

Sorrells, Russell B.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 11).Mode of ...

Wind-tunnel force and flow visualization data at Mach numbers from 1.6 to 4.63 for a series of bodies of revolution at angles of attack from -4 ̊to 60 ̊/

Landrum, Emma Jean.
Babb, C. Donald.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1979

Subject category 02."Langley Research Center.""March 1979"--Cover.Includes bibliographical reference...

Pressure data for four analytically defined arrow wings in supersonic flow /

Townsend, James C. (James Courtland), 1938-
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1980

Sept. 1980."Langley Research Center."Bibliography: p. 16.Mode of access: Internet

Wing-alone aerodynamic characteristics for high angles of attack at supersonic speeds /

Stallings, Robert L.
Lamb, Milton.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

"July 1982"--Cover."Langley Research Center."Includes bibliographical references.Mode of access: Int...

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 (...

Basic pressure measurements on a 0.0667-scale model of the North American X-15 research airplane at transonic speeds /

Osborne, Robert S.
Stafford, Virginia C.
Langley Research Center.
United States. National Aeronautics and Space Administration.

"Langley Research Center, Langely Field, Va.""October 1960."Cover title.Includes bibliographical ref...

Supersonic wings with significant leading-edge thrust at cruise /

Robins, A. Warner.
Mack, Robert J.
Carlson, Harry W.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1982

Subject Category 02."April 1980"--Cover."Langley Research Center."Includes bibliographical reference...

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

Loads induced on a flat plate at a Mach number of 4.5 with a sonic or supersonic jet exhausting normal to the surface /

Letko, William.
Langley Research Center.

Prepared at Langley Research Center."July 1963."Cover title.Includes bibliographical references (p. ...

Aerodynamic data on large semispan tilting wing with 0.4-diameter chord, single-slotted flap, and single propeller 0.22 chord below wing /

Fink, Marvin P.
United States. National Aeronautics and Space Administration.
Langley Research Center.

January 1969

Prepared at Langley Research Center.N 69-17312.Cover title.Includes bibliographical references (p. 1...

Wind-tunnel results for a modified 17-percent-thick low-speed airfoil section /

McGhee, Robert J.
Beasley, William D.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Langley Research Center.

January 1981

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

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

Abstract

Extracted data

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

Abstract

Extracted data

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