FORCE AND PRESSURE MEASUREMENTS ON SEVERAL CANOPY-FUSELAGE CONFIGURATIONS AT MACH NUMBERS 1.41 AND 2.01
Force and pressure measurements on several canopy- fuselage configurations at low supersonic speeds
PRESSURE MEASUREMENT↗
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PERFORMANCE OF A SUPERSONIC RAMP-TYPE SIDE INLET WITH RAM-SCOOP THROAT BLEED AND VARYING FUSELAGE BOUNDARY-LAYER REMOVAL MACH NUMBER RANGE 1.5 TO 2.0
Performance of supersonic ramp-type side inlet with ram-scoop throat bleed and varying fuselage boundary layer removal at low supersonic speeds
THROAT↗
INVESTIGATION OF STATIC PRESSURES AND BOUNDARY-LAYER CHARACTERISTICS ON THE FORWARD PARTS OF NINE FUSELAGES OF VARIOUS CROSS-SECTIONAL SHAPES AT M INFINITY EQUAL 2.01
Boundary layer characteristics of fuselages of various cross sectional shapes at static pressure
FUSELAGE↗
AERODYNAMICS OF A FAN-IN-FUSELAGE MODEL
Wind tunnel test of fan-in-fuselage model of vtol aircraft
WING↗
STABILITY AND CONTROL CHARACTERISTICS AT A MACH NUMBER OF 2.01 OF A SUPERSONIC VTOL AIRPLANE MODEL HAVING A BROAD FUSELAGE AND SMALL DELTA WINGS
Stability and control of supersonic vtol airplane model having broad fuselage and small delta wing
STABILITY AND CONTROL↗
Materials for Wings and Fuselage
Sheet materials for wing and fuselage of supersonic transports
FUSELAGE↗
Performance of a double-ramp side inlet with combinations of fuselage, ramp, and throat boundary-layer removal, mach number range, 1.5 to 2.0
Double-ramp side inlet with combinations of fuselage, ramp, and throat boundary layer removal
RAMP↗
Free-flight investigation of the drag of a 60 deg delta-wing configuration with large stores mounted below the indented fuselage at mach numbers between 0.8 and 1.6
Free flight drag measurements on delta wing with wing-fuselage-store
DRAG MEASUREMENT↗
Experimental and Theoretical Determination of Forces and Moments on a Store and on a Store- Pylon Combination Mounted on a 45 Deg Swept- Wing-Fuselage Configuration at a Mach Number of 1.61
Forces and moments of store-pylon combination mounting on swept wing-fuselage configuration in supersonic pressure tunnel
PYLON MOUNTING↗
Experimental flutter study of a wing-fuselage configuration at a mach number of 15.4 and comparison with theory
Helium flow at hypersonic speed used to calculate hypersonic flutter data on low aspect ratio, flexible, wing-fuselage configuration
LOW ASPECT RATIO WING↗
Effects of Boattail Area Contouring and Simulated Turbojet Exhaust on the Loading and Fuselage-tail Component Drag of a Twin-engine Fighter-type Airplane Model
Effects of boattail area contouring and simulated turbojet exhaust on loading and fuselage-tail component drag of twin-engine fighter-type airplane model
AERODYNAMIC LOAD↗
Measured and calculated flow conditions on the forward fuselage of the X-15 airplane and model at Mach numbers from 3.0 to 8.0
Measured and calculated flow conditions on forward fuselage of X-15 plane and model at Mach numbers from 3.0 to 8.0
FUSELAGE↗
Effects of wing-fuselage flow fields on missile loads at subsonic speeds
Swept wing-fuselage flow fields on missile loads at subsonic speeds
FLOW FIELD↗
Low-speed investigation of effects of vertical tails on the static stability characteristics of a canard-bomber configuration having a very thin wing and a slender elliptical fuselage
Effect of vertical tails on low speed static stability characteristics of canard-bomber configuration with very thin wing and slender elliptical fuselage
BOMBER AIRCRAFT↗
Some considerations regarding the application of the supersonic area rule to the design of airplane fuselages
Supersonic aircraft fuselage design for minimum wave drag
SUPERSONIC AIRCRAFT↗
Effect of skewed wing-tip controls on a variable-sweep wing-fuselage configuration
Skewed wing tip control effects on variable sweep wing-fuselage configuration
WING TIP CONTROL↗
An investigation of supersonic store interference in the vicinity of a 22 deg swept wing fuselage configuration at Mach numbers of 1.61 and 2.01
Pressure tunnel investigation of supersonic store interference in vicinity of 22 deg swept wing fuselage configuration at mach numbers 1.61 and 2.01
SWEPT WING↗
Effect of Fuselage and Tail Surfaces on Low-speed Yawing Characteristics of a Swept-wing Model as Determined in Curved-flow Test Section of Langley Stability Tunnel
Results are presented of a wind-tunnel investigation made to determine the influence of the fuselage and tail surfaces on the rotary derivatives in yawing flight of a transonic-airplane configuration having 45 degrees sweptback wing and tail surfaces. The tests were run in the curved-flow test section of the Langley stability tunnel at a Reynolds number of 1.07 X 10 to the sixth power and consisted of balance measurements throughout the angle-of-attack range for several flight-path radii of curvature. The results are compared with data from forced-oscillation and free-oscillation tests, and a description of testing techniques used is included.
WIND TUNNELS↗