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Transonic Flutter Investigation of Models of the Sweptback Wing of a Fighter Airplane
Effects of Components and Various Modifications on the Drag and the Static Stability and Control Characteristics of a 42 Deg Swept-Wing Fighter-Airplane Model at Mach Numbers of 1.60 to 2.50
Preliminary Free-Jet Performance of XRJ43-MA-3 Ram-Jet Engine at a Mach Number of 2.70
Preliminary Investigation of a Technique for Stability Studies of a Self-Propelled Model of a Submerged Submarine
Preliminary Transonic Flutter Investigation of Models of T-Tall of Blackburn NA-39 Airplane
Liquid Hydrogen as a Jet Fuel for High-Altitude Aircraft
Analysis of the Effects of Various Mass, Aerodynamic, and Dimensional Parameters on the Dynamic Lateral Stability of the Douglas D-558-2 Airplane
Summary of the Availability and Performance Problems of High Octane Number Fuels
Rocket-Powered Model Investigation of Lift, Drag, and Stability of a Body-Tail Configuration at Mach Numbers From 0.8 to 2.3 and Angles of Attack Between Plus or Minus 6.5 Degrees
Comparison of experimental with calculated results for the lifting effectiveness of a flexible 45 degree sweptback wing of aspect ratio 6.0 at Mach numbers from 0.8 to 1.3
Tests in the Ames 40- by 80-foot wind tunnel of the effects of varying wing modifications on the longitudinal characteristics of two-triangular wing airplane models with and without horizontal tails
Preliminary investigation of a technique for stability studies of a self-propelled model of a submerged submarine
Langley full-scale-tunnel investigation of the factors affecting the static lateral-stability characteristics of a typical fighter-type airplane
Preliminary Transonic Flutter Investigation of Models of T-Tail of Blackburn NA-39 Airplane
Effects of nose and afterbody modifications on aerodynamic characteristics of a body with and without a vertical tail at a Mach number of 2.01
Transonic Flutter Investigation of Models of the Sweptback Wing of a Fighter Airplane
Effects of shock-boundary-layer interaction on the performance of a long and a short subsonic annular diffuser
Jet effects on the base drag of a cylindrical afterbody with extended nozzles
An Exploratory Investigation at Mach Numbers of 2.50 and 2.87 of a Canard Bomber-Type Configuration Designed for Supersonic Cruise Flight
Low-Lift Drag of the Grumman F9F-9 Airplane as Obtained by a 1/7.5-Scale Rocket-Boosted Model and by Three 1/45.85-Scale Equivalent-Body Models Between Mach Numbers of 0.8 and 1.3, Ted No. NACA DE 391
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