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493
Experimental investigation of the simulation of atmospheric entry of ballistic missiles
Report presenting a small-scale apparatus for simulating the motion and heating of ballistic missiles and its elements of design and operation. Experiments demonstrate that conditions for simulation are fulfilled according to theoretical requirements. Results regarding the application to full-scale missiles, shadowgraph observations, observations of recovered models, and spectroscopic observations are provided.
Date:
December 12, 1957
Creator:
Neice, Stanford E.; Carson, James A. & Cunningham, Bernard E.
System:
The UNT Digital Library
In-Flight Gains Realized by Modifying a Twin Side-Inlet Induction System
Memorandum presenting an investigation of the effects of modifying a twin side-inlet duct system on an interceptor airplane as recorded and analyzed over an altitude range from about 25,000 to 51,000 feet throughout the transonic speed range to a Mach number of about 1.2. The modifications consisted primarily of redesigning the inlet lip, increasing the cross-sectional area of the inlet and diffuser, and adding a region of duct contraction ahead of the engine.
Date:
December 12, 1957
Creator:
Saltzman, Edwin J.
System:
The UNT Digital Library
In-flight gains realized by modifying a twin side-inlet induction system
Report presenting the effects of modifying a twin side-inlet duct system on an interceptor airplane over a range of altitudes throughout the transonic speed range to Mach number 1.2. The primary modifications were redesigning the inlet lip, increasing the cross-sectional area of the inlet and diffuser, and adding a region of duct contraction ahead of the engine.
Date:
December 12, 1957
Creator:
Saltzman, Edwin J.
System:
The UNT Digital Library
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
Memorandum presenting a wind-tunnel investigation of the three types of lateral control devices on a low-aspect-ratio trapezoidal wing. Tip ailerons, a plain spoiler, and a vented spoiler were investigated to ascertain the relative characteristics of each system. The results indicated the superiority in roll power of the tip ailerons over the plain and vented ailerons.
Date:
December 12, 1957
Creator:
Wong, Norman D.
System:
The UNT Digital Library
Theoretical and Experimental Investigation of Arbitrary Aspect Ratio, Supercavitating Hydrofoils Operating Near the Free Water Surface
Report presents a comparison of the theoretical and experimental expressions of lift, drag, and center of pressure of supercavitating hydrofoils. The results obtained from both methods appear to agree well with one another. The application of cavitation number to a variety of situations and speeds is also provided.
Date:
December 12, 1957
Creator:
Johnson, Virgil E., Jr.
System:
The UNT Digital Library
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
Report discussing the boundary-layer transition and heat-transfer measurements for a model of the Titan intercontinental ballistic missile up to a specified Mach and Reynolds number. Boundary-layer transition was observed on the nose of the missile. The drag coefficient for a variety of Mach numbers was also obtained.
Date:
December 19, 1957
Creator:
Graham, John B., Jr.; Chauvin, Leo T. & Speegle, Katherine C.
System:
The UNT Digital Library
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
"Boundary-layer transition and heat-transfer measurements were obtained 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 a Reynolds number per foot of 23 x 10(exp 6). Boundary-layer transition was observed on the nose of the model. Available theories predicted heat-transfer coefficients reasonably well for the fully laminar or turbulent flow conditions. The drag coefficient of the configuration was also obtained for a Mach number range of 1.25 to 3.75" (p. 1).
Date:
December 19, 1957
Creator:
Graham, John B., Jr.; Chauvin, Leo T. & Speegle, Katherine C.
System:
The UNT Digital Library
Comparison and Evaluation of Two Model Techniques Used in Predicting Bomb-Release Motions
"For the purpose of calculating bomb trajectories, forces and moments have been measured on bombs of three fineness ratios in the presence of a swept-wing fighter-bomber configuration at a Mach number of 1.61. Trajectories thus obtained have been compared with those from dynamic model tests and an analysis has been made to determine the source of errors and to suggest improvements in both techniques."
Date:
December 27, 1957
Creator:
Carlson, Harry W.; Geier, Douglas J. & Lee, John B.
System:
The UNT Digital Library
Comparison and Evaluation of Two Model Techniques Used in Predicting Bomb-Release Motions
"For the purpose of calculating bomb trajectories, forces and moments have been measured on bombs of three fineness ratio sin the presence of a swept-wing fighter bomber configuration at a Mach number of 1.61. Trajectories thus obtained have been compared with those from dynamic model tests and an analysis has been made to determine the source of errors and to suggest improvements in both techniques." (p. 1).
Date:
December 27, 1957
Creator:
Carlson, Harry W.; Geier, Douglas J. & Lee, John B.
System:
The UNT Digital Library
Experimental Hinge Moments on Two Freely Oscillating Trailing-Edge Controls Hinged at 55 Percent Control Chord
Memorandum presenting oscillatory hinge-moment characteristics obtained from free-flight tests of two rocket-powered models. Results indicate that the hinge-line location of 55 percent control chord did not prevent unstable control aerodynamic damping. The damping appeared to be more stabilizing as the amplitude of oscillation was increased.
Date:
December 27, 1957
Creator:
Martz, C. William
System:
The UNT Digital Library
Pressure Measurements on an Afterbody Behind Various Blunt Nose Shapes at a Mach Number of 2
Memorandum presenting an investigation of flow surrounding afterbodies behind blunt nose shapes at a Mach number of 2 in the 27- by 27-inch preflight jet. Pressure measurements were made on and around the afterbodies for each configuration.
Date:
December 27, 1957
Creator:
Speegle, Katherine C.
System:
The UNT Digital Library
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
Report presenting an investigation in the 20-foot free-spinning tunnel on a scale model to determine the spin and recovery characteristics of the Douglas F4D-1 airplane equipped with external fuel tanks. Results regarding erect spins, inverted spins, and parachute results are provided.
Date:
December 27, 1957
Creator:
Bowman, James S., Jr.
System:
The UNT Digital Library
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
Memorandum presenting an investigation in the 20-foot free-spinning tunnel on a scale model to determine the spin and recovery characteristics of the Douglas F4D-1 airplane with external wing fuel tanks installed. The results indicated that any fully developed erect spin obtained on the airplane with tanks installed will be satisfactorily terminated by rudder reversal accompanied by moving the ailerons to full with the spin.
Date:
December 27, 1957
Creator:
Bowman, James S., Jr.
System:
The UNT Digital Library