Miscellaneous directional-stability data for several airplane-like configurations from rocket-model tests at transonic speeds
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Purser, Paul E↗
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Some Effects of Body Cross-sectional Shape, Including Sunken-canopy Design, on Drag as Shown by Rocket-powered-model Tests at Mach Numbers from 0.8 to 1.5
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Stoney, William E , Jr↗
Effects of Wing Elasticity on the Aerodynamic Characteristics of an Airplane Configuration Having 45 Degrees Sweptback Wings as Obtained from Free-flight Rocket-model Tests at Transonic Speeds
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Vitale, A James↗
Comparison of lift-curve slopes for a model tested in two slotted tunnels of different sizes at high subsonic speeds
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Boswinkle, Robert W , Jr↗
Summary of Rocket-model Tests at Zero Lift of an Arrow-wing Missile Configuration from Mach Numbers of 0.9 to 1.8
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Arbic, Richard G↗
Some Effects of Aileron Span, Aileron Chord, and Wing Twist on Rolling Effectiveness as Determined by Rocket-powered Model Tests and Theoretical Estimates
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Strass, H Kurt↗
Collection and Summary of Flap-type-aileron Rolling-effectiveness Data at Zero Lift as Determined by Rocket-powered Model Tests at Mach Numbers Between 0.6 and 1.6
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Strass, H Kurt↗
Aerodynamic Characteristics at Mach Numbers from 0.7 to 1.75 of a Four-engine Swept-wing Airplane Configuration as Obtained from a Rocket-propelled Model Test
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Chapman, Rowe, Jr↗
Results of Rocket Model Test of an Airplane Configuration Having an Arrow Wing and Slender Flat-sided Fuselage : Lift, Drag, Longitudinal Stability, Lateral Force, and Jet Effects at Mach Numbers Between 1.0 and 2.3
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Peck, Robert F↗
Aerodynamic Heating of a Wing as Determined from a Free-flight Rocket-model Test to Mach Number 3.64
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Swanson, Andrew G↗
A Summary of the Longitudinal and Lateral Stability and Control Characteristics Obtained from Rocket-model Tests of a Swept-wing Fighter-type Airplane at Mach Numbers from 0.5 to 1.9
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Mitcham, Grady L↗
Model tests with a systematic series of 27 wing sections at full Reynolds number
A systematic series of 27 wing sections, characterized by a small travel of the center or pressure, have been investigated at 20 atmospheres pressure in the variable density wind tunnel of the National Advisory Committee for Aeronautics. The results are consistent with each other, and indicate that for such "stable" sections a small effective camber, a small effective S-shape and a thickness of 8 to 12 per cent lead to good aerodynamic properties.
Munk, Max M↗
The NACA Tank : A High-speed Towing Basin for Testing Models of Seaplane Floats
This report describes the high-speed model towing basin of the National Advisory Committee for Aeronautics, usually referred to as the NACA Tank. The purpose of this piece of equipment is to enable the Committee to provide information and data regarding the performance of seaplanes on the water analogous to the information furnished concerning the performance of airplanes in the air.
Truscott, Starr↗
Stability and Control Characteristics of a Fighter Airplane in Inverted Flight Attitude as Determined by Model Tests
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WINGS - DIHEDRAL↗
JRM-1 Landing Impact Characteristics from Model Tests
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SEAPLANES - IMPACT↗
The Effect of Spanwise Mass Distribution upon the Spin Characteristics of Airplanes as Determined by Model Tests Conducted in the Free-spinning Wind Tunnel
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Kamm, Robert W↗
Multiengine Airplane Spin Characteristics as Indicated by Model Tests in the Free-spinning Wind Tunnel
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Kamm, Robert W↗
Versatile Support For Electromagnetic-Test Model
Supporting apparatus holds model for measurements of electromagnetic properties. Includes rigid swept strut, on end of which model oriented over range of angles. Designed to interfere minimally with electromagnetic measurements.
Wood, Richard M.↗