Longitudinal aerodynamic characteristics at Mach 1.50 to 4.63 of a missile model employing various canards and a trailing edge flap control

An Experimental Investigation of the Static Longitudinal Stability and Control Characteristics of a Wingless Missile Configuration at Mach Numbers from 3.0 to 6.3

Gloria, H. R.

June 1958

Static longitudinal stability and control characteristics of wingless missile configuration at super...

Wind-Tunnel Investigation at a Mach Number of 2.01 of the Aerodynamic Characteristics in Combined Angles of Attack and Sideslip of Several Hypersonic Missile Configurations with Various Canard Controls

Robinson, R. B.

March 1958

An investigation of the aerodynamic characteristics of several hypersonic missile configurations wit...

Aerodynamic characteristics of a hypersonic research airplane concept having a 70 deg swept double-delta wing at Mach numbers from 0.80 to 1.20, with summary of data from 0.20 to 6.0

Penland, J. A.
Dillon, J. L.
Hallissy, J. B.

December 1979

The static longitudinal, lateral, and directional stability characteristics of a hypersonic research...

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

Wineman, Andrew R
Moul, Martin T

June 1952

A flight investigation has been made to determine the longitudinal stability and control characteris...

Longitudinal Stability and Control Characteristics as Determined by the Rocket-Model Technique for an Inline, Cruciform, Canard Missile Configuration with a Low-Aspect-Ratio Wing Having Trailing-Edge Flap Controls for a Mach Number Range of 0.7 to 1.8

Moul, M. T.
Baber, H. T., Jr.

September 1955

Two full-scale models of an inline, cruciform, canard missile configuration having a low-aspect-rati...

The Longitudinal Stability, Control Effectiveness, and Control Hinge Moment Characteristics Obtained from a Flight Investigation of a Canard Missile Configuration at Transonic and Supersonic Speeds

Niewald, Roy J
Moul, Martin T

November 1950

A 60 degree delta wing canard missile configuration was flight-tested at the Langley pilotless aircr...

Investigation of the Static Longitudinal Stability Characteristics of An Air-To-Surface Canard Missile Configuration in the Transonic Mach Number Range

Hunt, G. L.

October 1960

Static longitudinal stability and control characteristics of air-to-surface canard missile configura...

Supersonic aerodynamic characteristics of a low-aspect-ratio missile model with wing and tail controls and with tails in line and interdigitated

Graves, E. B.

April 1972

A study has been made to determine the aerodynamic characteristics of a low-aspect ratio cruciform m...

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, E. B.
Fournier, R. H.

July 1974

Investigations have been conducted in the Langley 8-foot transonic pressure tunnel and the Langley U...

Flight Investigation at Low Angles of Attack to Determine the Longitudinal Stability and Control Characteristics of a Cruciform Canard Missile Configuration with a Low-Aspect-Ratio Wing and Blunt Nose at Mach Numbers from 1.2 to 2.1

Brown, C. A., Jr.

September 1957

A full-scale rocket-powered model of a cruciform canard missile configuration with a low-aspect-rati...

Aerodynamic characteristic of a swept-wing cruise missile at Mach numbers from 0.50 to 2.86

Collins, I. K.
Spearman, M. L.

November 1972

An investigation has been made in the Mach number range from 0.50 to 2.86 to determine the longitudi...

Effect of tail-fin span on stability and control characteristics of a Canard-controlled missile at supersonic Mach numbers

Hernandez, G.
Allen, J. M.
Blair, A. B., Jr.

June 1983

An experimental wind-tunnel investigation was conducted at Mach numbers from 1.60 to 3.50 to obtain ...

NACA Research Memorandums

Presnell, John G., Jr.

July 1958

A brief investigation of the longitudinal stability and control effectiveness at supersonic speeds o...

Aerodynamic characteristics of a canard-controlled missile at Mach numbers of 0.8, 1.3, and 1.75

Wettlaufer, B.
Kassner, D. L.

July 1977

A typical missile model with nose-mounted canards and cruciform tail surfaces was tested in the Ames...

Aerodynamic characteristics of a hypersonic research airplane concept having a 70 degree swept double delta wing at Mach numbers from 1.50 to 2.86

Penland, J. A.
Marcum, D. C., Jr.
Fournier, R. H.

December 1975

An experimental investigation of the static longitudinal, lateral, and directional stability charact...

An Experimental Investigation of the Static Longitudinal Stability and Control Characteristics of a Wingless Missile Configuration at Mach Numbers from 3.0 to 6.3

Gloria, H. R.

June 1958

Static longitudinal stability and control characteristics of wingless missile configuration at super...

Wind-Tunnel Investigation at a Mach Number of 2.01 of the Aerodynamic Characteristics in Combined Angles of Attack and Sideslip of Several Hypersonic Missile Configurations with Various Canard Controls

Robinson, R. B.

March 1958

An investigation of the aerodynamic characteristics of several hypersonic missile configurations wit...

Aerodynamic characteristics of a hypersonic research airplane concept having a 70 deg swept double-delta wing at Mach numbers from 0.80 to 1.20, with summary of data from 0.20 to 6.0

Penland, J. A.
Dillon, J. L.
Hallissy, J. B.

December 1979

The static longitudinal, lateral, and directional stability characteristics of a hypersonic research...

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

Wineman, Andrew R
Moul, Martin T

June 1952

A flight investigation has been made to determine the longitudinal stability and control characteris...

Longitudinal Stability and Control Characteristics as Determined by the Rocket-Model Technique for an Inline, Cruciform, Canard Missile Configuration with a Low-Aspect-Ratio Wing Having Trailing-Edge Flap Controls for a Mach Number Range of 0.7 to 1.8

Moul, M. T.
Baber, H. T., Jr.

September 1955

Two full-scale models of an inline, cruciform, canard missile configuration having a low-aspect-rati...

The Longitudinal Stability, Control Effectiveness, and Control Hinge Moment Characteristics Obtained from a Flight Investigation of a Canard Missile Configuration at Transonic and Supersonic Speeds

Niewald, Roy J
Moul, Martin T

November 1950

A 60 degree delta wing canard missile configuration was flight-tested at the Langley pilotless aircr...

Investigation of the Static Longitudinal Stability Characteristics of An Air-To-Surface Canard Missile Configuration in the Transonic Mach Number Range

Hunt, G. L.

October 1960

Static longitudinal stability and control characteristics of air-to-surface canard missile configura...

Supersonic aerodynamic characteristics of a low-aspect-ratio missile model with wing and tail controls and with tails in line and interdigitated

Graves, E. B.

April 1972

A study has been made to determine the aerodynamic characteristics of a low-aspect ratio cruciform m...

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, E. B.
Fournier, R. H.

July 1974

Investigations have been conducted in the Langley 8-foot transonic pressure tunnel and the Langley U...

Flight Investigation at Low Angles of Attack to Determine the Longitudinal Stability and Control Characteristics of a Cruciform Canard Missile Configuration with a Low-Aspect-Ratio Wing and Blunt Nose at Mach Numbers from 1.2 to 2.1

Brown, C. A., Jr.

September 1957

A full-scale rocket-powered model of a cruciform canard missile configuration with a low-aspect-rati...

Aerodynamic characteristic of a swept-wing cruise missile at Mach numbers from 0.50 to 2.86

Collins, I. K.
Spearman, M. L.

November 1972

An investigation has been made in the Mach number range from 0.50 to 2.86 to determine the longitudi...

Effect of tail-fin span on stability and control characteristics of a Canard-controlled missile at supersonic Mach numbers

Hernandez, G.
Allen, J. M.
Blair, A. B., Jr.

June 1983

An experimental wind-tunnel investigation was conducted at Mach numbers from 1.60 to 3.50 to obtain ...

NACA Research Memorandums

Presnell, John G., Jr.

July 1958

A brief investigation of the longitudinal stability and control effectiveness at supersonic speeds o...

Aerodynamic characteristics of a canard-controlled missile at Mach numbers of 0.8, 1.3, and 1.75

Wettlaufer, B.
Kassner, D. L.

July 1977

A typical missile model with nose-mounted canards and cruciform tail surfaces was tested in the Ames...

Aerodynamic characteristics of a hypersonic research airplane concept having a 70 degree swept double delta wing at Mach numbers from 1.50 to 2.86

Penland, J. A.
Marcum, D. C., Jr.
Fournier, R. H.

December 1975

An experimental investigation of the static longitudinal, lateral, and directional stability charact...

An Experimental Investigation of the Static Longitudinal Stability and Control Characteristics of a Wingless Missile Configuration at Mach Numbers from 3.0 to 6.3

Gloria, H. R.

June 1958

Static longitudinal stability and control characteristics of wingless missile configuration at super...

Wind-Tunnel Investigation at a Mach Number of 2.01 of the Aerodynamic Characteristics in Combined Angles of Attack and Sideslip of Several Hypersonic Missile Configurations with Various Canard Controls

Robinson, R. B.

March 1958

An investigation of the aerodynamic characteristics of several hypersonic missile configurations wit...

Aerodynamic characteristics of a hypersonic research airplane concept having a 70 deg swept double-delta wing at Mach numbers from 0.80 to 1.20, with summary of data from 0.20 to 6.0

Penland, J. A.
Dillon, J. L.
Hallissy, J. B.

December 1979

The static longitudinal, lateral, and directional stability characteristics of a hypersonic research...

Longitudinal aerodynamic characteristics at Mach 1.50 to 4.63 of a missile model employing various canards and a trailing edge flap control

Abstract

Extracted data

Longitudinal aerodynamic characteristics at Mach 1.50 to 4.63 of a missile model employing various canards and a trailing edge flap control

Abstract

Extracted data

Related items

Related items