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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
Dynamic stability and control characteristics of a vertically rising airplane model in hovering flight
No Description digital.library.unt.edu/ark:/67531/metadc58803/
Fundamental flame velocities of pure hydrocarbons I : alkanes, alkenes, alkynes benzene, and cyclohexane
The flame velocities of 37 pure hydrocarbons including normal and branched alkanes, alkenes, and alkynes; as well as benzene and cyclohexane, together with the experimental technique employed are presented. The normal alkanes have about the same flame velocity from ethane through heptane with methane being about 16 percent lower. Unsaturation increases the flame velocity in the order of alkanes, alkenes, and alkynes. Branching reduces the flame velocity. digital.library.unt.edu/ark:/67531/metadc58576/
The effects of fuel sloshing on the lateral stability of a free-flying airplane model
No Description digital.library.unt.edu/ark:/67531/metadc57576/
Additional Studies of the Stability and Controllability of an Unswept-Wing Vertically Rising Airplane Model in Hovering Flight Including Studies of Various Tethered Landing Techniques
No Description digital.library.unt.edu/ark:/67531/metadc58981/
Dynamic Stability and Control Characteristics of a Delta-Wing Vertically Rising Airplane Model in Take-Offs, Landings and Hovering Flight
No Description digital.library.unt.edu/ark:/67531/metadc59023/
Static directional stability of a tandem-helicopter fuselage
No Description digital.library.unt.edu/ark:/67531/metadc58553/
Effect of the proximity of the ground on the stability and control characteristics of a vertically rising airplane model in the hovering condition
No Description digital.library.unt.edu/ark:/67531/metadc58957/
Take-Off and Landing Characteristics of a 0.13-Scale Model of the Convair XFY-1 Vertically Rising Airplane in Steady Winds, TED No. NACA DE 368
An experimental investigation has been conducted to determine the stability and control characteristics of a 0.13-scale free-flight model of the Convair XFY-1 airplane during take-offs and landings in steady winds. The tests indicated that take-offs in headwinds up to at least 20 knots (full scale) will be fairly easy to perform although the airplane may be blown downstream as much as 3 spans before a trim condition can be established. The distance that the airplane will be blown down-stream can be reduced by restraining the upwind landing gear until the instant of take-off. The tests also indicated that spot landings in headwinds up to at least 30 knots (full scale) and in crosswinds up to at least 20 knots (full scale) can be accomplished with reasonable accuracy although, during the landing approach, there will probably be an undesirable nosing-up tendency caused by ground effect and by the change in angle of attack resulting from vertical descent. Some form of arresting gear will probably be required to prevent the airplane from rolling downwind or tipping over after contact. This rolling and tipping can be prevented by a snubbing line attached to the tip of the upwind' wing or tail or by an arresting gear consisting of a wire mesh on the ground and hooks on the landing gear to engage the mesh. digital.library.unt.edu/ark:/67531/metadc64599/
Stability and control flight tests of a 0.13-scale model of the consolidated-Vultee XFY-1 airplane in take-offs, landings, and hovering flight : TED No. NACA DE 368
No Description digital.library.unt.edu/ark:/67531/metadc59405/
Altitude performance of a 20-inch-diameter ram-jet engine investigated in a free-jet facility at Mach number 3.0
No Description digital.library.unt.edu/ark:/67531/metadc53178/
Design of combustor for long-range ram-jet engine and performance of rectangular analog
No Description digital.library.unt.edu/ark:/67531/metadc53174/
Preliminary transient performance data on the fuel control of the XRJ47-W-5 ram-jet engine
No Description digital.library.unt.edu/ark:/67531/metadc53179/
Full-scale, free-jet investigation of methods of improving outlet flow distribution in a side-inlet supersonic diffuser
No Description digital.library.unt.edu/ark:/67531/metadc53176/
Investigation of three low-temperature-ratio combustor configurations in a 48-inch-diameter ram-jet engine
No Description digital.library.unt.edu/ark:/67531/metadc53173/
Radiant heat transfer from flames in a single tubular turbojet combuctor
No Description digital.library.unt.edu/ark:/67531/metadc53295/
Experimental investigation of laminar-boundary-layer control on an airfoil section equipped with suction slots located at discontinuities in the surface pressure distribution
No Description digital.library.unt.edu/ark:/67531/metadc53185/
Experimental investigation of effects of simulated nacelles and wing-root freedoms on supersonic flutter characteristics of a cambered, modified, swept, tapered wing
No Description digital.library.unt.edu/ark:/67531/metadc53182/
Experimental investigation of the stability, control, and induced rolling moments of a canard missile airframe at a Mach number of 1.7
No Description digital.library.unt.edu/ark:/67531/metadc53181/
A preliminary study of the effect of boric oxide deposits on the performance of two selected turbine stator-blade shapes
No Description digital.library.unt.edu/ark:/67531/metadc53187/
Transonic wind-tunnel investigation of static- pressure fluctuations in duct of a scale inlet model of a supersonic fighter-bomber airplane
No Description digital.library.unt.edu/ark:/67531/metadc53180/
Interference effects of fuselage-stored missiles on inlet duct model of an interceptor-type aircraft at Mach numbers 1.5 to 1.9
No Description digital.library.unt.edu/ark:/67531/metadc53188/
Calculated performance of a direct-air nuclear turbojet-powered airplane using a split-flow reactor and a separated-type shield
No Description digital.library.unt.edu/ark:/67531/metadc53184/
Experimental investigation of extreme internal flow turning at the cowl lip of an axisymetric inlet at a Mach number of 2.95
No Description digital.library.unt.edu/ark:/67531/metadc53189/
A flight and analog study of the effect of elevating the radar-boresight axis upon stability and tracking performance of an automatically controlled interceptor
No Description digital.library.unt.edu/ark:/67531/metadc53186/
Comparison and evaluation of two model techniques used in predicting bomb-release motions
No Description digital.library.unt.edu/ark:/67531/metadc53155/
Wind-Tunnel Flutter Tests at Mach Numbers up to 3.0 of Boeing Wing Models for Weapons System 110A
No Description digital.library.unt.edu/ark:/67531/metadc53151/
An investigation of ejection releases of submerged and semisubmerged dynamically scaled stores from a simulated bomb bay of a fighter- bomber airplane at supersonic speeds
No Description digital.library.unt.edu/ark:/67531/metadc53157/
Longitudinal aerodynamic characteristics of various configurations of a revised 1/22-scale model of the Republic F-105 airplane at Mach numbers of 1.41 and 2.01
No Description digital.library.unt.edu/ark:/67531/metadc53276/
Compilation and Analysis of US Turbojet and Ram-Jet Engine Characteristics
No Description digital.library.unt.edu/ark:/67531/metadc53273/
A method for calculating the lift and center of pressure of wing-body-tail combinations at subsonic, transonic, and supersonic speeds
No Description digital.library.unt.edu/ark:/67531/metadc53575/
The subsonic lateral and longitudinal static stability characteristics up to large angles of sideslip for a triangular-wing airplane model having a ventral fin
No Description digital.library.unt.edu/ark:/67531/metadc53199/
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
No Description digital.library.unt.edu/ark:/67531/metadc53196/
Effect of throat bleed on the supersonic performance of a half-conical side-inlet system
No Description digital.library.unt.edu/ark:/67531/metadc53193/
Results of the flight test of a 0.13-scale rocket-boosted model of the McDonnell F4H-1 airplane between Mach numbers of 0.20 and 1.90
No Description digital.library.unt.edu/ark:/67531/metadc53275/
Free Spinning and Recovery Characteristics of 1/36-Scale Model of the Republic F-105B Airplane
No Description digital.library.unt.edu/ark:/67531/metadc53272/
Experimental Investigation of Flutter and Divergence Characteristics of the Rocket-Motor Fin of the ASROC Missile
No Description digital.library.unt.edu/ark:/67531/metadc53271/
Investigation of a 1/22-Scale Model of the Republic F-105 Airplane in the Langley 8-Foot Transonic Tunnel Lateral, Directional, and Additional Longitudinal Static Stability and Control
No Description digital.library.unt.edu/ark:/67531/metadc53277/
Wind-Tunnel Investigation of the Effect of Spin on the Aerodynamic Characteristics of a 60-Millimeter T-24 Mortar Shell with Several Tail-Fin Configurations
No Description digital.library.unt.edu/ark:/67531/metadc53270/
Transonic Aerodynamic Characteristics of a 1/15-Scale Model of the Convair B-58 Airplane
No Description digital.library.unt.edu/ark:/67531/metadc53278/
Heat-Transfer and Pressure Measurements from a Flight Test of the Second 1/18-Scale Model of the Titan Intercontinental Ballistic Missile up to a Mach Number of 3.91 and Reynolds Number Per Foot of 23.4 by 10 to the 6th Power
No Description digital.library.unt.edu/ark:/67531/metadc53274/
Investigation of the Kingfisher XAUM-2 Flying Torpedo in the Langley Full Scale Tunnel, Ted No. NACA DE 327
No Description digital.library.unt.edu/ark:/67531/metadc53279/
Induction system characteristics and engine surge occurrence for two fighter-type airplanes
No Description digital.library.unt.edu/ark:/67531/metadc53165/
Wind-tunnel investigation of a 1/6-scale model of the Bumblebee XPM missile at high subsonic speeds
No Description digital.library.unt.edu/ark:/67531/metadc53162/
Analysis of a liquid-metal turbine-propeller cycle for propulsion of low-speed nuclear- powered aircraft
No Description digital.library.unt.edu/ark:/67531/metadc53161/
A comparison of the maneuvering performance of a monowing versus a cruciform missile
No Description digital.library.unt.edu/ark:/67531/metadc53167/
Analysis of a nuclear-powered liquid-metal ducted-fan cycle
No Description digital.library.unt.edu/ark:/67531/metadc53160/
Pressure measurements on an afterbody behind various blunt nose shapes at a Mach number of 2
No abstract available. digital.library.unt.edu/ark:/67531/metadc53168/
Organophosphorus compounds in rocket-engine applications
No Description digital.library.unt.edu/ark:/67531/metadc53164/
The Sodium Hydroxide Reactor - Effect of Reactor Variables on Criticality and Fuel- Element Temperature Requirements for Subsonic and Supersonic Aircraft Nuclear Propulsion
No abstract available. digital.library.unt.edu/ark:/67531/metadc53169/
High-altitude performance of J71-A-11 turbojet engine and its components using JP-4 and gaseous-hydrogen fuels
No Description digital.library.unt.edu/ark:/67531/metadc53166/
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