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NACA Research Memorandums
493
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1957
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Comparison and Evaluation of Two Model Techniques Used in Predicting Bomb-Release Motions
Comparison and Evaluation of Two Model Techniques Used in Predicting Bomb-Release Motions
Experimental Hinge Moments on Two Freely Oscillating Trailing-Edge Controls Hinged at 55 Percent Control Chord
Pressure Measurements on an Afterbody Behind Various Blunt Nose Shapes at a Mach Number of 2
Supplementary Investigation in the Langley 20-Foot Free-Spinning Tunnel of a 1/20-Scale Model of the Douglas F4D-1 Airplane With External Wing Fuel Tanks
Supplementary Investigation in the Langley 20-Foot Free-Spinning Tunnel of a 1/20-Scale Model of the Douglas F4D-1 Airplane With External Wing Fuel Tanks: TED No. NACA AD 3116
Heat-Transfer and Pressure Measurements from a Flight Test of a 1/18-Scale Model of the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.95 and Reynolds Number Per Foot of 23 by 10 to the 6th Power
Heat-Transfer and Pressure Measurements From a Flight Test of a 1/18-Scale Model of the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.95 and Reynolds Number Per Foot of 23 X 10(Exp 6): Coord. No. AF-AM-70
The effects of boundary-layer separation over bodies of revolution with conical tail flares
Experimental investigation of the simulation of atmospheric entry of ballistic missiles
In-Flight Gains Realized by Modifying a Twin Side-Inlet Induction System
In-flight gains realized by modifying a twin side-inlet induction system
An Investigation of the Control Effectiveness of Tip Ailerons and Spoilers on a Low-Aspect-Ratio Trapezoidal-Wing Airplane Model at Mach Numbers From 1.55 to 2.35
Theoretical and Experimental Investigation of Arbitrary Aspect Ratio, Supercavitating Hydrofoils Operating Near the Free Water Surface
Aerodynamic load distribution over a 45 degree swept wing having a spoiler-slot-deflector aileron and other spoiler ailerons for Mach numbers from 0.60 to 1.03
Flight Investigation of the Transonic Longitudinal and Lateral Handling Qualities of the Douglas X-3 Research Airplane
Investigation at High Subsonic Speeds of the Use of Low Auxiliary Tail Surfaces Having Dihedral to Improve the Longitudinal and Directional Stability of a T-Tail Model at High Lift
Normal-force and hinge-moment characteristics at transonic speeds of flap-type ailerons at three spanwise locations on a 4-percent-thick sweptback-wing-body model and pressure distribution measurements on an inboard aileron
Aerodynamic characteristics at Mach number of 4.06 of a typical supersonic airplane model using body and vertical-tail wedges to improve directional stability
Aerodynamic Characteristics of a Model of an Escape Capsule for a Supersonic Bomber-Type Airplane at a Mach Number of 2.49
Effects of string-support interference on the drag of an olgive-cylinder body with and without a boatail at 0.6 to 1.4 Mach number
Investigation at High Subsonic Speeds of the Static Longitudinal and Lateral Stability Characteristics of Two Canard Airplane Configurations
Endurance Evaluation of Sintered, Porous, Strut-Supported Turbine Blades made by Federal-Mogul-Bower-Bearings, Incorporated, under Bureau of Aeronautics Contract NOas 55-124-C
Effects of vertical location of wing and horizontal tail on the aerodynamic characteristics in pitch at Mach numbers from 0.60 to 1.40 of an airplane configuration with an unswept wing
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