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NACA Research Memorandums
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NACA Research Memorandums
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1955
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1955
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The Effect of Base Bleed on the Base Pressure, Lift, Drag, and Pitching Moment of a 10-Percent-Thick Blunt-Base Airfoil at a Mach Number of 2.72
Flight Characteristics of a Wingless Rocket- Powered Model With Four Externally Mounted Air-to-Air Missiles at Mach Numbers 0.7 to 1.6
Free-flight investigation, including some effects of wing aeroelasticity, of the rolling effectiveness of an all-movable horizontal tail with differential incidence at Mach numbers from 0.6 to 1.5
Investigation of Two Short Annular Diffuser Configurations Utilizing Section and Injection as a Means of Boundary-Layer Control
A limited flight investigation of the effect of dynamic vibration absorbers on the response of an airplane structure during buffeting
Analysis of V-G records from ten types of Navy airplanes in squadron operations during the period 1949 to 1953
Development of a new flutter testing technique using a towed dynamic airplane model equipped with an automatic stabilizing system: Experimental and calculated dynamic stability characteristics for speeds up to 200 mph
Effects of Free-Flight Rocket-Model Booster-Adapter Configurations on the Aerodynamic Characteristics in Pitch and Sideslip of a Swept-Wing Fighter Airplane Model at a Mach Number of 2.01
Effects of free-flight rocket-model booster-adapter configurations on the aerodynamic characteristics in pitch and sideslip of a swept-wing fighter airplane model at a Mach number of 2.01
Flight-determined pressure distributions over a section of the 35 degree swept wing of the Douglas D-558-II research airplane at Mach numbers up to 2.0
Preliminary Results of an Investigation at Transonic Speeds to Determine the Effects of a Heated Propulsive Jet on the Drag Characteristics of a Related Series of Afterbodies
Aerodynamic characteristics of a 60 degree delta wing having a half-delta tip control at a Mach number of 4.04
Lift, drag, and longitudinal stability at Mach numbers from 0.8 to 2.1 of a rocket-powered model having a tapered unswept wing of aspect ratio 3 and inline tail surfaces
Lift, drag, and static longitudinal stability characteristics of four airplane-like configurations at Mach numbers from 3.00 to 6.28
Wind-Tunnel Measurements at Subsonic Speeds of the Static and Dynamic-Rotary Stability Derivatives of a Triangular-Wing Airplane Model Having a Triangular Vertical Tail
The Effect of Wing Fences on the Longitudinal Characteristics at High Subsonic Speeds of a Wing-Fuselage-Tail Combination Having a Wing With 40 Degrees of Sweepback and NACA Four-Digit Thickness Distribution
The effect of wing height on the longitudinal characteristics at high subsonic speeds of a wing-fuselage-tail combination having a wing with 40 degrees of sweepback and NACA four digit thickness distribution
Effects of spanwise location of sweep discontinuity on the low-speed static lateral stability characteristics of a complete model with wings of M and W plan form
Experimental Static Aerodynamic Forces and Moments at Low Speed on a Missile Model During Simulated Launching From the 25-Percent-Semispan and Wing-Tip Location of a 45 Degree Sweptback Wing-Fuselage Combination
Flight measurements of wing loads on the Convair XF-92A delta-wing airplane
Low-Speed Investigation of the Effects of Wing Tanks and Speed Brakes on the Static Stability of a Model Having a 40 Degree Swept Wing
Additional measurements of the low-speed static stability of a configuration employing three triangular wing panels and a body of equal length
Experimental investigation of a transonic axial-flow-compressor rotor with double-circular-arc airfoil blade sections 3: comparison of blade-element performance with three levels of solidity
Investigation of the effects of body indentation and of wing-plan-form modification on the longitudinal characteristics of a 60 degree swept-wing-body combination at Mach numbers of 1.41, 1.61, and 2.10
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