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wind tunnels

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View Study of optical techniques for the Ames unitary wind tunnels By Lee, George.

Study of optical techniques for the Ames unitary wind tunnels

Study of optical techniques for the Ames unitary wind tunnels

By Lee, George.

View Recommended Practice By American Institute of Aeronautics and As
Cover of Recommended Practice by american institute of aeronautics and as

Recommended Practice

By American Institute of Aeronautics and As

View Hot-jet simulation in cryogenic wind tunnels By Keisuke Asai

Hot-jet simulation in cryogenic wind tunnels

Hot-jet simulation in cryogenic wind tunnels

By Keisuke Asai

View Wind-tunnel investigation of aerodynamic loading on a 0.237-scale model of a remotely piloted research vehicle with a thick, high-aspect-ratio supercritical wing By Thomas A. Byrdsong

Wind-tunnel investigation of aerodynamic loading on a 0.237-scale model of a remotely piloted research vehicle with a thick, high-aspect-ratio supercritical wing

Wind-tunnel investigation of aerodynamic loading on a 0.237-scale model of a remotely piloted research vehicle with a thick, high-aspect-ratio supercritical wing

By Thomas A. Byrdsong

View Wind Tunnel Testing of High-Rise Buildings By Peter Irwin

Wind Tunnel Testing of High-Rise Buildings

Wind Tunnel Testing of High-Rise Buildings

By Peter Irwin

View KC-135 Winglet Program Review By KC-135 Winglet Program Review (1981 Edwards, Calif.)

KC-135 Winglet Program Review

KC-135 Winglet Program Review

By KC-135 Winglet Program Review (1981 Edwards, Calif.)

View Langley 8-ft. HTT test 139 gas analyses By Danny R. Sprinkle

Langley 8-ft. HTT test 139 gas analyses

Langley 8-ft. HTT test 139 gas analyses

By Danny R. Sprinkle

View Wind-tunnel pressure 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 ̊ By Emma Jean Landrum

Wind-tunnel pressure 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 ̊

Wind-tunnel pressure 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 ̊

By Emma Jean Landrum

View Wind-tunnel testing By Alan Pope

Wind-tunnel testing

Wind-tunnel testing

By Alan Pope

View 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 ̊ By Emma Jean Landrum

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 ̊

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 ̊

By Emma Jean Landrum

View Wind-tunnel testing By Pope, Alan

Wind-tunnel testing

Wind-tunnel testing

By Pope, Alan

View Evaluation of wind-tunnel gust response technique correlations with analytical and flight test results By L. Tracy Redd

Evaluation of wind-tunnel gust response technique correlations with analytical and flight test results

Evaluation of wind-tunnel gust response technique correlations with analytical and flight test results

By L. Tracy Redd

View Wind-tunnel technique By R. C. Pankhurst

Wind-tunnel technique

Wind-tunnel technique

By R. C. Pankhurst

View Wind-tunnel test of an articulated helicopter rotor model with several tip shapes By John D. Berry

Wind-tunnel test of an articulated helicopter rotor model with several tip shapes

Wind-tunnel test of an articulated helicopter rotor model with several tip shapes

By John D. Berry

View Finite-rate water condensation in combustion-heated wind tunnels By Wayne D. Erickson

Finite-rate water condensation in combustion-heated wind tunnels

Finite-rate water condensation in combustion-heated wind tunnels

By Wayne D. Erickson

View Results of tests performed on the acoustic quiet flow facility three-dimensional model tunnel By P. S. Barna

Results of tests performed on the acoustic quiet flow facility three-dimensional model tunnel

Results of tests performed on the acoustic quiet flow facility three-dimensional model tunnel

By P. S. Barna

View The design of test-section inserts for higher speed aeroacoustic testing in the Ames 80- by 120-foot wind tunnel By Paul T. Soderman

The design of test-section inserts for higher speed aeroacoustic testing in the Ames 80- by 120-foot wind tunnel

The design of test-section inserts for higher speed aeroacoustic testing in the Ames 80- by 120-foot wind tunnel

By Paul T. Soderman

View Aeronautical facilities catalogue By Frank E. Peñaranda

Aeronautical facilities catalogue

Aeronautical facilities catalogue

By Frank E. Peñaranda

View Wind-tunnel investigation of aerodynamic loading on a 0.237-scale model of a remotely piloted research vehicle with a thick, high-aspect-ratio supercritical wing By Thomas A Byrdsong

Wind-tunnel investigation of aerodynamic loading on a 0.237-scale model of a remotely piloted research vehicle with a thick, high-aspect-ratio supercritical wing

Wind-tunnel investigation of aerodynamic loading on a 0.237-scale model of a remotely piloted research vehicle with a thick, high-aspect-ratio supercritical wing

By Thomas A Byrdsong

View Wind-tunnel investigation of an advanced general aviation canard configuration By Joseph R. Chambers

Wind-tunnel investigation of an advanced general aviation canard configuration

Wind-tunnel investigation of an advanced general aviation canard configuration

By Joseph R. Chambers

View X-29A longitudinal and directional force and moment supplemental transonic wind tunnel test results By Albion H. Bowers

X-29A longitudinal and directional force and moment supplemental transonic wind tunnel test results

X-29A longitudinal and directional force and moment supplemental transonic wind tunnel test results

By Albion H. Bowers

View NASA Lewis 9-by 15-foot low-speed wind tunnel user manual By Ronald H. Soeder

NASA Lewis 9-by 15-foot low-speed wind tunnel user manual

NASA Lewis 9-by 15-foot low-speed wind tunnel user manual

By Ronald H. Soeder

View On-line analysis capabilities developed to support the AFW wind-tunnel tests By Carol D. Wieseman

On-line analysis capabilities developed to support the AFW wind-tunnel tests

On-line analysis capabilities developed to support the AFW wind-tunnel tests

By Carol D. Wieseman

View A three-dimensional orthogonal laser velocimeter for the NASA Ames 7- by 10-foot wind tunnel By Stephen E. Dunagan

A three-dimensional orthogonal laser velocimeter for the NASA Ames 7- by 10-foot wind tunnel

A three-dimensional orthogonal laser velocimeter for the NASA Ames 7- by 10-foot wind tunnel

By Stephen E. Dunagan