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Experimental Static Aerodynamic Forces and Moments at High Subsonic Speeds on a Missile Model During Simulated Launching From the Midsemispan Location of a 45 Degree Sweptback Wing-Fuselage-Pylon Combination

Description: "An investigation was made at high subsonic speeds in the Langley high-speed 7- by 10-foot tunnel to determine the static aerodynamic forces and moments on a missile model during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage-pylon combination. The results indicated significant variations in all the aerodynamic components with changes in chordwise location of the missile. Increasing the angle of attack caused increases in the induced effects on the miss… more
Date: January 10, 1957
Creator: Alford, William J., Jr. & King, Thomas J., Jr.
Partner: UNT Libraries Government Documents Department
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The interaction of boundary layer and compression shock and its effect upon airfoil pressure distributions

Description: Report presenting an investigation of the mechanism of interaction of compression shock with boundary layer. Shockless pressure distributions at supercritical Mach numbers were found to be accounted for by a marked thickening of the boundary layer for some distance ahead of a shock wave.
Date: April 10, 1947
Creator: Allen, H. Julian; Heaslet, Max A. & Nitzberg, Gerald E.
Partner: UNT Libraries Government Documents Department
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The Effect of Compression Ratio on Knock Limits of High-Performance Fuels in a CFR Engine 3: Blends of 2,3-Dimethylpentane With 28-R

Description: Report discussing the knock-limited performance of blends of 2,3-dimethylpentane and 23-R fuel in an F-4 engine at three sets of conditions and three compression ratios. The knock-limited performance of 2,3-dimethylpentane has about the same sensitivity to compression ratio and inlet-air temperature as 28-R fuel.
Date: February 10, 1945
Creator: Alquist, Henry E. & Tower, Leonard K.
Partner: UNT Libraries Government Documents Department
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An Investigation at Low Speed of a Large-Scale Triangular Wing of Aspect Ratio Two 2: The Effect of Airfoil Section Modifications and the Determination of the Wake Downwash

Description: Report presenting a study of the characteristics of a large-scale triangular wing to include the effects of section modifications. The wing in this report is the same as the one in the previous report but features various degrees of rounding of the wing leading edge and wing maximum thickness rather than having sharp edges. Results regarding the effects of airfoil section modifications, visible trailing vortices, and surveys in the extended chord plane are provided.
Date: December 10, 1947
Creator: Anderson, Adrien E.
Partner: UNT Libraries Government Documents Department
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Tests of NACA 65(216)-420 and 66(218)-420 Airfoils at High Speeds

Description: Report presenting wind tunnel tests of NACA 65(216)-420 and 66(218)-420 airfoils at speeds up to and slightly above the critical. Section coefficients of lift, drag, and pitching-moment and extensive pressure-distribution data are presented. The critical speed for these airfoils at their design life coefficient of 0.4 is shown to be about 460 miles per hour at seal level and about 415 miles per hour at 25,000 feet altitude.
Date: April 10, 1944
Creator: Anderson, Joseph L.
Partner: UNT Libraries Government Documents Department
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Some Measurements of Flying Qualities of a Douglas D-558-II Research Airplane During Flights to Supersonic Speeds

Description: Report presenting some measurements of the dynamic lateral stability and lateral and longitudinal trim of a Douglas D-558-II in flights up to a Mach number of 1.87 and an altitude of about 67,000 feet. Testing indicated that the airplane flying in low density air at supersonic speeds had poor dynamic lateral stability, which worsened as the Mach number was increased to 1.85.
Date: March 10, 1953
Creator: Ankenbruck, Herman O. & Dahlen, Theodore E.
Partner: UNT Libraries Government Documents Department
open access

Hydrodynamic Directional Behavior of a Swept Planing-Tail Hull

Description: "A qualitative investigation of the low-speed directional behavior of a swept planing-tail hull was made in the Langley tank no. 2 in still water and still air with the use of a free self-propelled model. The configuration was directionally unstable over a range of low speed. It was, however, directionally controllable at all speeds by use of the rudder and elevator. Several modifications that were investigated did not improve the controllability" (p. 1).
Date: January 10, 1952
Creator: Arabian, Donald D.
Partner: UNT Libraries Government Documents Department
open access

Free-Flight Longitudinal-Stability Investigation Including Some Effects of Wing Elasticity From Mach Numbers of 0.85 to 1.34 of a Tailless Missile Configuration Having a 45 Degree Sweptback Wing of Aspect Ratio 5.5

Description: Report presenting a free-flight longitudinal-stability investigation between Mach numbers of 0.85 and 1.34 to obtain the aerodynamic characteristics of a long-range, jet-propelled, ground-to-ground missile with a wing of aspect ratio 5.5, 45 degrees of sweepback, and taper ratio 0.4 on a body with a vertical tail. Two models with two different wing materials were flown. Results regarding trimmed flight, pitching flight, and aeroelastic calculations are provided.
Date: August 10, 1953
Creator: Arbic, Richard G. & Gillespie, Warren, Jr.
Partner: UNT Libraries Government Documents Department
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A study of the torque equilibrium of an autogiro rotor

Description: From Summary: "Two improvements have been made in the method developed in NACA Reports nos. 487 and 591 for the estimation of the inflow velocity required to overcome a given decelerating torque in an autogiro rotor. At low tip-speed ratios, where the assumptions necessary for the analytical integrations of the earlier papers are valid, the expressions therein derived are greatly simplified by combining and eliminating terms with a view of minimizing the numerical computations required. At high… more
Date: January 10, 1938
Creator: Bailey, F. J., Jr.
Partner: UNT Libraries Government Documents Department
open access

An Analysis of the Effect of Structural Feedback on the Flutter of a Control Surface Having a Power-Boost System

Description: From Summary: "Such devices as leading- and trailing-edge flaps which are now in use on operational aircraft permit the attainment of maximum airplane lift coefficients, power-off, of the order of 2.8 (reference 1). Airfoil-section maximum lift coefficients as high as 5.5 have been obtained in wind-tunnel tests (see, for example, reference 2), and in a limited flight investigation airplane lift coefficients of 4.2 were obtained (reference 3)."
Date: June 10, 1952
Creator: Barnes, Robert H.
Partner: UNT Libraries Government Documents Department
open access

Flight Test of a Radial-Burning Solid-Fuel Ram Jet

Description: Report presenting an investigation of a rocket-launched ram-jet engine with radial-burning solid fuel. Results regarding acceleration, altitude, durability of the fuel, net and gross thrust coefficients, and overall fuel specific impulse are provided.
Date: December 10, 1952
Creator: Bartlett, Walter A., Jr. & Dettwyler, H. Rudolph
Partner: UNT Libraries Government Documents Department
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A Preliminary Investigation at Mach Number 1.91 of an Inlet Configuration Designed for Insensitivity to Positive Angle-of-Attack Operation

Description: Report presenting an investigation to determine the pressure-recovery and mass-flow characteristics of an inlet configuration designed to be less sensitive to positive angle-of-attack operation than a conventional conical inlet. Results regarding the straight plate, plate swept 47.5, plates swept 42 degrees and 24 degrees, perforated plates, and a general comparison are provided.
Date: July 10, 1953
Creator: Beheim, Milton A.
Partner: UNT Libraries Government Documents Department
open access

Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the Grumman XF9F-2 Airplane with Wing-Tip Tanks Installed

Description: "An investigation of the spin and recovery characteristics of a 1/24-scale model of the Grumman XF9F-2 airplane with wing-tip tanks installed has been conducted-in the Langley 20-foot free-spinning tunnel. The effects of control settings and movements on the erect spin and recovery characteristics of the model for a range of possible loadings of the tip tanks were determined. Spin and recovery characteristics without tanks were determined in a previous investigation" (p. 1).
Date: June 10, 1949
Creator: Berman, Theodore & Wilson, Jack H.
Partner: UNT Libraries Government Documents Department
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Friction, wear, and surface damage of metals as affected by solid surface films

Description: "As predicted by friction theory, experiments showed that friction and surface damage of metals can be reduced by solid surface films. The ability of materials to form surface films that prevent welding was a very important factor in wear of dry and boundary lubricated surfaces. Films of graphitic carbon on cast irons, NiO on nickel alloys, and FeO and Fe(sub 3)O(sub 4) on ferrous materials were found to be beneficial. Abrasive films such as Fe(sub 2)O(sub 3) or MoO(sub 3) were definitely detri… more
Date: February 10, 1955
Creator: Bisson, Edmond E.; Johnson, Robert L.; Swikert, Max A. & Godfrey, Douglas
Partner: UNT Libraries Government Documents Department
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Facilities and methods used in full-scale airplane crash-fire investigation

Description: The report includes a description of the test facilities and methods, crash configuration, layout of crash site, instrumentation, data-recording systems, and the post-crash examination procedure of the fullscale crash-fire investigation, which is part of a comprehensive study of the airplane crash-fire problem.
Date: March 10, 1952
Creator: Black, Dugald O.
Partner: UNT Libraries Government Documents Department
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Free-Flight Aerodynamic-Heating Data to Mach Number 10.4 for a Modified Von Karman Nose Shape

Description: Report presenting aerodynamic-heating data obtained on a modified-fineness-ratio-5.0 Von Karman nose shape at free-stream Mach numbers up to 10.4 with a rocket-propelled model. Transient skin temperatures were measured on the nose, and a maximum temperature of 1,663 degrees R was measured after maximum Mach number was obtained.
Date: July 10, 1956
Creator: Bland, William M., Jr. & Collie, Katherine A.
Partner: UNT Libraries Government Documents Department
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Investigation at High Subsonic Speeds of Methods of Alleviating the Adverse Interference at the Root of a Swept-Back Wing

Description: Memorandum presenting an investigation of the interference at the root of a sweptback wing at high subsonic Mach numbers by means of wind-tunnel measurements of a wing-body combination with the 50-percent-chord line of the wing either unswept or swept back 35 degrees. Results regarding body characteristics, pressure studies, tuft studies, and force studies are provided.
Date: August 10, 1950
Creator: Boddy, Lee E.
Partner: UNT Libraries Government Documents Department
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The Sodium Hydroxide Reactor - Effect of Reactor Variables on Criticality and Fuel- Element Temperature Requirements for Subsonic and Supersonic Aircraft Nuclear Propulsion

Description: Report presenting two-group criticality calculations for sodium-hydroxide-cooled, moderated, and reflected reactors for various concentrations and compositions of reactor fuel-element structural material. The investigation was performed in order to determine the applicability of the fuel properties to power a nuclear aircraft. Results regarding the specific reactor calculations, reflector savings, criticality generalization, typical neutron flux and heat-generation distributions, static stabili… more
Date: February 10, 1953
Creator: Bogart, Donald & Valerino, Michael F.
Partner: UNT Libraries Government Documents Department
open access

The Sodium Hydroxide Reactor: Effect of Reactor Variables on Criticality and Fuel-Element Temperature Requirements for Subsonic and Supersonic Aircraft Nuclear Propulsion

Description: Report presenting results of two-group criticality calculations for sodium-hydroxide-cooled, moderated, and reflected reactors for various concentrations and compositions of reactor fuel-element structural material. Based on turbojet-engine cycle operating conditions optimized for minimum airplane gross weight, the maximum reactor fuel-element and coolant temperatures are related to the reactor heat release and airplane gross weight for a range of reactor heat-transfer variables.
Date: February 10, 1953
Creator: Bogart, Donald & Valerino, Michael F.
Partner: UNT Libraries Government Documents Department
open access

Analysis of parameters for thrust control of a turbojet engine equipped with air-inlet throttle and variable-area exhaust nozzle

Description: From Introduction: "In this report, altitude, airplane velocity, exhaust-nozzle area, and turbine-inlet temperature were chosen and corresponding engine speed, fuel flow, and throttle pressure ratio were found. A detailed discussion of the engine analysis and the calculations used are presented in Appendix A. The derivations of the principal equations used are presented in appendix B."
Date: August 10, 1948
Creator: Boksenbom, Aaron S. & Feder, Melvin S.
Partner: UNT Libraries Government Documents Department
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Free-Flight Skin Temperature and Pressure Measurements on a Slightly Blunted 25 Deg Cone-Cylinder-Flare Configuration to a Mach Number of 9.89

Description: "Skin temperatures and surface pressures have been measured on a slightly blunted cone-cylinder-flare configuration to a maximum Mach number of 9.89 with a rocket-propelled model. The cone had a total angle of 25 deg and the flare had a 10 deg half-angle. Temperature data were obtained at eight cone locations, four cylinder locations, and seven flare locations; pressures were measured at one cone location, one cylinder location, and three flare locations" (p. 1).
Date: April 10, 1957
Creator: Bond, Aleck C. & Rumsey, Charles B.
Partner: UNT Libraries Government Documents Department
open access

Flutter Experiments With Various Control Configurations

Description: Report discussing the flutter characteristics of several control-surface configurations, including a wing with tip ailerons, an all-movable stabilizer, vertical tails with trailing-edge rudders, a t-tail, and some simple models of all-movable controls. Some trends of the configurations and suggestions for improving the flutter characteristics are provided.
Date: July 10, 1957
Creator: Boswinkle, Robert W., Jr. & Morgan, Homer G.
Partner: UNT Libraries Government Documents Department
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Emergency Spin-Recovery Device for the 1/18-Scale Model of the Ryan X-13 Airplane as Determined from Tests in the Langley 20-Foot Free-Spinning Tunnel

Description: An investigation has been conducted in the Langley 20-foot free-spinning tunnel on a l/18-scale model of the Ryan X-13 airplane to determine the size parachute required for emergency-spin recovery during demonstration spins. Test results for erect spins indicate that a stable 12.73-foot-diameter parachute with a drag coefficient of 1.11 (based on the 12.73-foot projected diameter) is the minimum size required to insure satisfactory recovery in an emergency. The use of a stable parachute is reco… more
Date: January 10, 1955
Creator: Bowman, James S., Jr.
Partner: UNT Libraries Government Documents Department
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Static stability and control of canard configurations at Mach numbers from 0.70 to 2.22: triangular wing and canard on an extended body

Description: Report presenting an investigation of the static stability and control characteristics of a canard airplane configuration without analysis for a range of Mach numbers from 0.70 to 2.22. This configuration consisted of a triangular wing and triangular canard, a low aspect ratio vertical tail, and a modified Sears-Haack body. Data are presented for various combinations of the body, canard, wing, and vertical tail at severla angles of sideslip, angles of attack, and canard deflection angles.
Date: February 10, 1958
Creator: Boyd, John W. & Peterson, Victor L.
Partner: UNT Libraries Government Documents Department
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