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NACA Research Memorandums
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NACA Research Memorandums
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1950-1959
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1958
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Low-Speed Wind-Tunnel Tests of a 1/8-Scale Model of the Bell D-188A VTOL Airplane
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
Stability of Ballistic Reentry Bodies
Flight, Analog-Simulator, and Analytical Studies of an Automatically Controlled Interceptor Which Uses a Bank-Angle-Error Computer for Lateral Commands
Aerodynamic Heating of Blunt Nose Shapes at Mach Numbers Up to 14
Summary of Flight Data Obtained From 0.12-Scale Rocket-Powered Models of the Chance Vought Regulus 2 Missile
Experimental and Analytical Investigation of the Transonic and Supersonic Divergence Characteristics of a Delta-Plan-Form All-Movable Control
Performance of an All-internal Conical Compression Inlet With Annular Throat Bleed at Mach Number 5.0
Dynamic Lateral Behavior of High-Performance Aircraft
Aerodynamic heating of blunt nose shapes at Mach numbers up to 14
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
The static longitudinal characteristics of a twisted and cambered 45 degree sweptback wing at Mach numbers up to 0.96
Use of Shock-Trap Bleed to Improve Pressure Recovery of Fixed-and Variable-Capture-Area Internal-Contraction Inlets; Mach Number 2.0 to 3.0
Flight investigation of the low-speed characteristics of a 45 degree swept-wing fighter-type airplane with blowing boundary-layer control applied to the trailing edge flaps
Forces and pitching moments on an aspect-ratio-3.1 wing-body combination at Mach numbers from 2.5 to 3.5 and sublimation studies of the effect of single-elements roughness on the boundary-layer flow
Dynamic lateral behavior of high-performance aircraft
Experimental investigation of the effect of yaw on rates of heat transfer to transverse circular cylinders in a 6500-foot-per-second hypersonic air stream
Analysis of effects of interceptor roll performance and maneuverability on success of collision-course attacks
Wind-Tunnel Investigation of the Effect of Sweep and Taper Ratio on Effectiveness of Spoiler-Slot-Deflector Controls on Aspect-Ratio-4 Wings at Transonic Speeds
Wind-Tunnel Investigation of the Low-Speed Stability and Performance Characteristics of a Jet-Powered Low-Aspect-Ratio Vertical-Take-Off-and-Landing Configuration With Engines Buried in Tiltable Wings
Aerodynamic characteristics at Mach numbers 2.36 and 2.87 of an airplane configuration having a cambered arrow wing with a 75 degree swept leading edge
Flight Investigation of a Full-Scale Aircraft Ejector with Various Spacing Ratios and Correlation with Small-Scale Tests
Performance of an All-Internal Conical Compression Inlet with Annular Throat Bleed at Mach Number 5.0
Longitudinal and lateral aerodynamic characteristics at combined angles of attack and sideslip of a generalized missile model having a rectangular wing at a Mach number of 4.08
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