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

Pressure distributions on three different cruciform aft-tail control surfaces of a wingless missile at mach 1.60, 2.36, and 3.70 Volume 1: Trapezoidal tail

Babb, C. D.
Wassum, D. L.
Sawyer, W. C.
Lamb, M.

August 1979

The results of pressure distribution tests conducted in the Langley Unitary Plan wind tunnel are pre...

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...

Effect of fin planform on the aerodynamic characteristics of a wingless missile with AFT cruciform controls at Mach 1.60, 2.36, and 2.86

Trescot, C. D., Jr.
Foster, G. V.
Babb, C. D.

July 1973

An investigation was made in the Langley Unitary Plan wind tunnel to determine the effects of fin pl...

Supersonic aerodynamic characteristics of a rocket-vehicle model with low-aspect-ratio wing and tail surfaces

Graves, E. B.

March 1971

Supersonic aerodynamic characteristics of rocket vehicle model with low aspect ratio wing and tail s...

Stability and control characteristics of a monoplannar missile configuration with two low-profile tail arrangements at Mach numbers from 1.70 to 2.86

Blair, A. B., Jr.

August 1977

An experimental wind tunnel investigation has been made to determine the longitudinal and lateral ae...

Supersonic aerodynamic characteristics of a tail-control cruciform maneuverable missile with and without wings

Spearman, M. L.

January 1983

The aerodynamic characteristics for a winged and wingless cruciform missile configuration were exami...

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

Trescot, C. D., Jr.

October 1971

Wind tunnel static longitudinal stability and control characteristics of cruciform delta winged miss...

Aerodynamic Characteristics at a Mach Number of 6.8 of Two Hypersonic Missile Configurations, One with Low-Aspect-Ratio Cruciform Fins and Trailing-Edge Flaps and One with a Flared Afterbody and All-Movable Controls

Robinson, R. B.
Bernot, P. T.

August 1958

An investigation has been made to determine the aerodynamic characteristics in pitch at a Mach numbe...

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...

AERODYNAMIC CHARACTERISTICS OF MISSILE CONFIGURATIONS WITH WINGS OF LOW ASPECT RATIO FOR VARIOUS COMBINATIONS OF FOREBODIES, AFTERBODIES, AND NOSE SHAPES FOR COMBINED ANGLES OF A_vfACK AND SIDESLIP AT A MACH NUMBER OF 2.01

Rm Ldi
Research Memoran Du M
B. Robinson
Wash I Ngton
B. Robinson

January 1957

An investigation has been made in the Langley 4- by 4-foot super-sonic pressure tunnel to determine ...

Stability and control characteristics of a monoplanar missile configuration with two low-profile tail arrangements at Mach numbers from 1.70 to 2.86 /

Blair, A. B.
United States. National Aeronautics and Space Administration.

January 1977

An experimental wind tunnel investigation has been made to determine the longitudinal and lateral ae...

Longitudinal Aerodynamic Characteristics to Large Angles of Attack of a Cruciform Missile Configuration at a Mach Number of 2

Spahr, J. R.

December 1954

The lift, pitching-moment, and drag characteristics of a missile configuration having a body of fine...

FREE-FLIGHT INVESTIGATION AT TRANSONIC SPEEDS OF THE STABILITY CHARACTERISTICS OF A TAILLESS MISSILE CONFIGURATION HAVING A 45 DEG SWEPTBACK WING OF ASPECT RATIO 4

Arbic, R. G.

August 1956

Free flight test of tailless missile configuration with 45-deg sweptback wing of aspect ratio 4 - st...

Stability and control characteristics of a monoplane missile with large delta wings and various tail controls at Mach 1.90 to 2.86

Jernell, L. S.

July 1974

Wind tunnel tests were conducted to determine the stability and control characteristics of a monopla...

Aerodynamic Characteristics of Missile Configurations with Wings of Low Aspect Ratio for Various Combinations of Forebodies, Afterbodies, and Nose Shapes for Combined Angles of Attack and Sideslip at a Mach Number of 2.01

Robinson, Ross B

June 1957

An investigation has been made in the Langley 4-by-4-foot supersonic pressure tunnel to determine th...

Pressure distributions on three different cruciform aft-tail control surfaces of a wingless missile at mach 1.60, 2.36, and 3.70 Volume 1: Trapezoidal tail

Babb, C. D.
Wassum, D. L.
Sawyer, W. C.
Lamb, M.

August 1979

The results of pressure distribution tests conducted in the Langley Unitary Plan wind tunnel are pre...

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...

Effect of fin planform on the aerodynamic characteristics of a wingless missile with AFT cruciform controls at Mach 1.60, 2.36, and 2.86

Trescot, C. D., Jr.
Foster, G. V.
Babb, C. D.

July 1973

An investigation was made in the Langley Unitary Plan wind tunnel to determine the effects of fin pl...

Supersonic aerodynamic characteristics of a rocket-vehicle model with low-aspect-ratio wing and tail surfaces

Graves, E. B.

March 1971

Supersonic aerodynamic characteristics of rocket vehicle model with low aspect ratio wing and tail s...

Stability and control characteristics of a monoplannar missile configuration with two low-profile tail arrangements at Mach numbers from 1.70 to 2.86

Blair, A. B., Jr.

August 1977

An experimental wind tunnel investigation has been made to determine the longitudinal and lateral ae...

Supersonic aerodynamic characteristics of a tail-control cruciform maneuverable missile with and without wings

Spearman, M. L.

January 1983

The aerodynamic characteristics for a winged and wingless cruciform missile configuration were exami...

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

Trescot, C. D., Jr.

October 1971

Wind tunnel static longitudinal stability and control characteristics of cruciform delta winged miss...

Aerodynamic Characteristics at a Mach Number of 6.8 of Two Hypersonic Missile Configurations, One with Low-Aspect-Ratio Cruciform Fins and Trailing-Edge Flaps and One with a Flared Afterbody and All-Movable Controls

Robinson, R. B.
Bernot, P. T.

August 1958

An investigation has been made to determine the aerodynamic characteristics in pitch at a Mach numbe...

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...

AERODYNAMIC CHARACTERISTICS OF MISSILE CONFIGURATIONS WITH WINGS OF LOW ASPECT RATIO FOR VARIOUS COMBINATIONS OF FOREBODIES, AFTERBODIES, AND NOSE SHAPES FOR COMBINED ANGLES OF A_vfACK AND SIDESLIP AT A MACH NUMBER OF 2.01

Rm Ldi
Research Memoran Du M
B. Robinson
Wash I Ngton
B. Robinson

January 1957

An investigation has been made in the Langley 4- by 4-foot super-sonic pressure tunnel to determine ...

Stability and control characteristics of a monoplanar missile configuration with two low-profile tail arrangements at Mach numbers from 1.70 to 2.86 /

Blair, A. B.
United States. National Aeronautics and Space Administration.

January 1977

An experimental wind tunnel investigation has been made to determine the longitudinal and lateral ae...

Longitudinal Aerodynamic Characteristics to Large Angles of Attack of a Cruciform Missile Configuration at a Mach Number of 2

Spahr, J. R.

December 1954

The lift, pitching-moment, and drag characteristics of a missile configuration having a body of fine...

FREE-FLIGHT INVESTIGATION AT TRANSONIC SPEEDS OF THE STABILITY CHARACTERISTICS OF A TAILLESS MISSILE CONFIGURATION HAVING A 45 DEG SWEPTBACK WING OF ASPECT RATIO 4

Arbic, R. G.

August 1956

Free flight test of tailless missile configuration with 45-deg sweptback wing of aspect ratio 4 - st...

Stability and control characteristics of a monoplane missile with large delta wings and various tail controls at Mach 1.90 to 2.86

Jernell, L. S.

July 1974

Wind tunnel tests were conducted to determine the stability and control characteristics of a monopla...

Aerodynamic Characteristics of Missile Configurations with Wings of Low Aspect Ratio for Various Combinations of Forebodies, Afterbodies, and Nose Shapes for Combined Angles of Attack and Sideslip at a Mach Number of 2.01

Robinson, Ross B

June 1957

An investigation has been made in the Langley 4-by-4-foot supersonic pressure tunnel to determine th...

Pressure distributions on three different cruciform aft-tail control surfaces of a wingless missile at mach 1.60, 2.36, and 3.70 Volume 1: Trapezoidal tail

Babb, C. D.
Wassum, D. L.
Sawyer, W. C.
Lamb, M.

August 1979

The results of pressure distribution tests conducted in the Langley Unitary Plan wind tunnel are pre...

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...

Effect of fin planform on the aerodynamic characteristics of a wingless missile with AFT cruciform controls at Mach 1.60, 2.36, and 2.86

Trescot, C. D., Jr.
Foster, G. V.
Babb, C. D.

July 1973

An investigation was made in the Langley Unitary Plan wind tunnel to determine the effects of fin pl...

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

Abstract

Extracted data

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

Abstract

Extracted data

Related items

Related items