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Theoretical Analysis of the Interference Effects of Several Supersonic Tunnel Walls Capable of Absorbing the Shock Caused by the Nose of a Model
Flight Determination of the Longitudinal Stability and Control Characteristics of the Bell X-5 Research Airplane at 58.7 Degrees Sweepback
The Effect of Blunt-Trailing-Edge Modifications on the High-Speed Stability and Control Characteristics of a Swept-Wing Fighter Airplane
Fabrication and Properties of Hot-Pressed Molybdenum Disilicide
Induction System Characteristics and Engine Surge Occurrence for Two Fighter-Type Airplanes
Further investigation of NACA 4-(5)(08)-03 two-blade propeller at high forward speeds
Wing-dropping characteristics of some straight and swept wings at transonic speeds as determined with rocket-powered models
Effects of a Fuselage and Various High-Lift and Stall-Control Flaps on Aerodynamic Characteristics in Pitch of an NACA 64-Series 40 Degree Swept-Back Wing
Theoretical performance of some rocket propellants containing hydrogen, nitrogen, and oxygen
Experimental investigation of hot-gas bleedback for ice protection of turbojet engines 2: nacelle with long straight air inlet
Investigation of several clamshell variable-area exhaust nozzles for turbojet engines
Flight Investigation of the Aileron Characteristics of the Douglas D-558-I Airplane (BuAero No. 37972) at Mach Numbers Between 0.6 and 0.89
Static longitudinal and lateral stability and control characteristics of a model of a 35 degree swept-wing airplane at a Mach number of 1.41
A Wind-Tunnel Investigation at High Subsonic Speeds of the Lateral Control Characteristics of Various Plain Spoiler Configurations on a 3-Percent-Thick 60 Degree Delta Wing
Experimental Investigation at High Subsonic Speeds of the Rolling Stability Derivatives of a Complete Model with an Aspect-Ratio-2.52 Wing Having an Unswept 72-Percent-Chord Line and a High Horizontal tail
Lateral stability and control characteristics of the Convair XF-92A delta-wing airplane as measured in flight
Light Diffusion Through High-Speed Turbulent Boundary Layers
Large-scale wind-tunnel tests of an airplane model with a 45 degree sweptback wing of aspect ratio 2.8 employing high-velocity blowing over the leading- and trailing-edge flaps
Induction system characteristics and engine surge occurrence for two fighter-type airplanes
Some Effects of Roughness on Stagnation-Point Heat Transfer at a Mach Number of 2, a Stagnation Temperature of 3,530 F, and a Reynolds Number of 2.5 X 10(Exp 6) Per Foot
Wind-Tunnel Investigation at a Mach Number of 2.01 of Forebody Strakes for Improving Directional Stability of Supersonic Aircraft
Theoretical analysis of the interference effects of several supersonic-tunnel walls capable of absorbing the shock caused by the nose of a model
Aerodynamic characteristics of various configurations of a model of a 45 degree swept-wing airplane at a Mach number of 2.01
Spin and Recovery Characteristics of the Curtiss-Wright XP-87 Airplane
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