Effects of fineness and closure ratios on boattail drag of circular-arc afterbody models with jet exhaust at Mach numbers up to 1.3 /

The effect of canard and vertical tails on the aerodynamic characteristics of a model with a 59 ̊sweptback wing at a Mach number of 0.30 /

Henderson, William P.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 8).Mode of a...

Influence of base modifications on in-flight base drag in the presence of jet exhaust for Mach numbers from 0.7 to 1.5 /

Powers, Sheryll Goecke.
Ames Research Center.

January 1988

Prepared at Ames Research Center."February 1988"--Cover.Includes bibliographical references (p. 6).M...

Effect of boattail juncture shape on pressure drag coefficients of isolated afterbodies

Shrewsbury, G. D.

March 1968

Effect of boattail juncture shape on pressure drag coefficients of isolated afterbodies of supersoni...

Effect of fineness ratio on boattail drag of circular-arc afterbodies having closure ratios of 0.50 with jet exhaust at Mach numbers up to 1.30 /

Reubush, David E.
Runckel, Jack F.
Langley Research Center.

January 1973

Prepared at Langley Research Center.Cover title.Bibliography: p. 20-21.Mode of access: Internet

Effects of fineness and closure ratios on boattail drag of circular-arc-afterbody models with jet exhaust at Mach numbers up to 1.3

Reubush, D. E.

May 1973

The effects of variations in fineness ratio and closure ratio on the boattail drag of circular-arc a...

Effect of Reynolds number on the subsonic boattail drag of several wing-body configurations /

Reubush, David E.
United States. National Aeronautics and Space Administration.
Langley Research Center.

January 1976

Cover title.Includes bibliographical references (p. 8-9).Mode of access: Internet

Effect of fineness ratio on boattail drag of circular-arc afterbodies having closure ratios of 0.50 with jet exhaust at Mach numbers up to 1.30

Runckel, J. F.
Reubush, D. E.

May 1973

An investigation was conducted to determine the effect of fineness ratio on the drag of circular-arc...

Jet effects on the drag of conical afterbodies at spersonic speeds /

Compton, William B.
Langley Research Center.

January 1972

Prepared at Langley Research Center.Cover title.Bibliography: p. 13.Mode of access: Internet

Experimental study of the effectiveness of cylindrical plume simulators for predicting jet-on boattail drag at Mach numberes up to 1.30 /

Reubush, David E.
Lanlgely Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 17-19).Mode ...

Effects of afterbody boattail design and empennage arrangement on aeropropulsive characteristics of a twin-engine fighter model at transonic speeds /

Bangert, Linda S.
Reubush, David E.
Leavitt, Laurence D.
Langley Research Center.

Prepared at Langley Research Center."June 1987"--Cover.Includes bibliographical references (p. 13).M...

Effects of boattailing and nozzle extension on the thrust-minus-drag of a multiple-jet configuration. /

Scott, William R.
United States. National Aeronautics and Space Administration.

The investigation was conducted at Mach numbers from 0.60 to 1.40 and jet total-pressure ratios from...

Flight Reynolds number effects on a contoured boattail nozzle at subsonic speeds /

Chamberlin, Roger.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 8-9).Mode of a...

A free-flight investigation of the effects of simulated sonic turbojet exhaust on the drag of a boattail body with various jet sizes from Mach number 0.87 to 1.50 /

Falanga, Ralph A.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1955

Three 7.5 degree boattail bodies of revolution with varying base-annulus areas and jet sizes provide...

An investigaion of boattail geometry and Reynolds number effects on forebody and afterbody drag at transonic Mach numbers /

Spratley, A. V., author.
United States. Air Force. Systems Command. issuing body.
Arnold Engineering Development Center, sponsor.
ARO, Inc., sponsor.

An experimental investigation was conducted in the AEDC 16-foot Transonic Wind Tunnel (16T) to deter...

A parametric study of effect of forebody shape on flow angularity at Mach 8 /

Johnson, Charles B.
Marcum, Don C.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 12-13).Mode ...

The effect of canard and vertical tails on the aerodynamic characteristics of a model with a 59 ̊sweptback wing at a Mach number of 0.30 /

Henderson, William P.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 8).Mode of a...

Influence of base modifications on in-flight base drag in the presence of jet exhaust for Mach numbers from 0.7 to 1.5 /

Powers, Sheryll Goecke.
Ames Research Center.

January 1988

Prepared at Ames Research Center."February 1988"--Cover.Includes bibliographical references (p. 6).M...

Effect of boattail juncture shape on pressure drag coefficients of isolated afterbodies

Shrewsbury, G. D.

March 1968

Effect of boattail juncture shape on pressure drag coefficients of isolated afterbodies of supersoni...

Effect of fineness ratio on boattail drag of circular-arc afterbodies having closure ratios of 0.50 with jet exhaust at Mach numbers up to 1.30 /

Reubush, David E.
Runckel, Jack F.
Langley Research Center.

January 1973

Prepared at Langley Research Center.Cover title.Bibliography: p. 20-21.Mode of access: Internet

Effects of fineness and closure ratios on boattail drag of circular-arc-afterbody models with jet exhaust at Mach numbers up to 1.3

Reubush, D. E.

May 1973

The effects of variations in fineness ratio and closure ratio on the boattail drag of circular-arc a...

Effect of Reynolds number on the subsonic boattail drag of several wing-body configurations /

Reubush, David E.
United States. National Aeronautics and Space Administration.
Langley Research Center.

January 1976

Cover title.Includes bibliographical references (p. 8-9).Mode of access: Internet

Effect of fineness ratio on boattail drag of circular-arc afterbodies having closure ratios of 0.50 with jet exhaust at Mach numbers up to 1.30

Runckel, J. F.
Reubush, D. E.

May 1973

An investigation was conducted to determine the effect of fineness ratio on the drag of circular-arc...

Jet effects on the drag of conical afterbodies at spersonic speeds /

Compton, William B.
Langley Research Center.

January 1972

Prepared at Langley Research Center.Cover title.Bibliography: p. 13.Mode of access: Internet

Experimental study of the effectiveness of cylindrical plume simulators for predicting jet-on boattail drag at Mach numberes up to 1.30 /

Reubush, David E.
Lanlgely Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 17-19).Mode ...

Effects of afterbody boattail design and empennage arrangement on aeropropulsive characteristics of a twin-engine fighter model at transonic speeds /

Bangert, Linda S.
Reubush, David E.
Leavitt, Laurence D.
Langley Research Center.

Prepared at Langley Research Center."June 1987"--Cover.Includes bibliographical references (p. 13).M...

Effects of boattailing and nozzle extension on the thrust-minus-drag of a multiple-jet configuration. /

Scott, William R.
United States. National Aeronautics and Space Administration.

The investigation was conducted at Mach numbers from 0.60 to 1.40 and jet total-pressure ratios from...

Flight Reynolds number effects on a contoured boattail nozzle at subsonic speeds /

Chamberlin, Roger.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 8-9).Mode of a...

A free-flight investigation of the effects of simulated sonic turbojet exhaust on the drag of a boattail body with various jet sizes from Mach number 0.87 to 1.50 /

Falanga, Ralph A.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1955

Three 7.5 degree boattail bodies of revolution with varying base-annulus areas and jet sizes provide...

An investigaion of boattail geometry and Reynolds number effects on forebody and afterbody drag at transonic Mach numbers /

Spratley, A. V., author.
United States. Air Force. Systems Command. issuing body.
Arnold Engineering Development Center, sponsor.
ARO, Inc., sponsor.

An experimental investigation was conducted in the AEDC 16-foot Transonic Wind Tunnel (16T) to deter...

A parametric study of effect of forebody shape on flow angularity at Mach 8 /

Johnson, Charles B.
Marcum, Don C.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 12-13).Mode ...

The effect of canard and vertical tails on the aerodynamic characteristics of a model with a 59 ̊sweptback wing at a Mach number of 0.30 /

Henderson, William P.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 8).Mode of a...

Influence of base modifications on in-flight base drag in the presence of jet exhaust for Mach numbers from 0.7 to 1.5 /

Powers, Sheryll Goecke.
Ames Research Center.

January 1988

Prepared at Ames Research Center."February 1988"--Cover.Includes bibliographical references (p. 6).M...

Effect of boattail juncture shape on pressure drag coefficients of isolated afterbodies

Shrewsbury, G. D.

March 1968

Effect of boattail juncture shape on pressure drag coefficients of isolated afterbodies of supersoni...

Effects of fineness and closure ratios on boattail drag of circular-arc afterbody models with jet exhaust at Mach numbers up to 1.3 /

Abstract

Extracted data

Effects of fineness and closure ratios on boattail drag of circular-arc afterbody models with jet exhaust at Mach numbers up to 1.3 /

Abstract

Extracted data

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