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Preliminary Evaluation of the Wing Leading Edge as a Missile-Mounting Location

Description: Report discussing testing to evaluate some of the major aspects of mounting and launching missiles from the leading edge of a wing, including experimentation with six missile models at several Mach numbers. Information from flight tests and launching tests is provided.
Date: January 16, 1957
Creator: Hill, P. R. & Hoffman, S.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Control Signals for Variable Ramps of Twin-Duct Side Inlets

Description: Report presenting an investigation to determine the effectiveness of experimental control signals applied to a theoretical inlet throat Mach number control system and normal-shock-position control system for varying the inlet geometry of a twin-duct prototype aircraft. Results regarding inlet instability, control requirements, individual throat Mach number control signals, average throat Mach number control signals, theoretical thraot Mach number control analysis, effect of angle of attack, and… more
Date: January 16, 1958
Creator: Beheim, Milton A. & Yeager, Richard A.
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation of a High Subsonic Mach Number Turbine Having a 40-Blade Rotor With Zero Suction-Surface Diffusion

Description: Memorandum presenting an experimental turbine designed for a high weight flow per unit frontal area, a high specific work output, a relative critical velocity ratio of 0.82 at the rotor hub inlet, and zero rotor blade suction-surface diffusion. Results regarding a comparison of overall performance of subject turbine with that of configurations I and II and comparison of rotor blade momentum thickness of subject turbine with that of configurations I and II are provided.
Date: January 16, 1958
Creator: Nusbaum, William J.; Wasserbauer, Charles A. & Hauser, Cavour H.
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation of a 7-Inch-Tip-Diameter Transonic Turbine

Description: Memorandum presenting the overall performance results obtained for a 7-inch transonic turbine and a comparison with the results of a 14-inch turbine of geometrically similar design that had been previously investigated. The peak efficiency obtained with the turbine was 0.85, which was 2 points lower than that obtained previously with the 14-inch turbine.
Date: January 16, 1958
Creator: Whitney, Warren J. & Wintucky, William T.
Partner: UNT Libraries Government Documents Department
open access

A Device for Measuring Sonic Velocity and Compressor Mach Number

Description: "A device has been developed which measures the velocity of sound in fluids at stagnation and is especially adaptable to turbine and compressor testing for which the constituency of the working fluid may be in doubt. By utilizing the shaft frequency of a rotary compressor, the instrument can also be used to provide a direct measurement of the compressor Mach number (ratio of blade-tip velocity to inlet velocity of sound at stagnation). A Helmholtz resonator is employed in the measurement of the… more
Date: January 16, 1947
Creator: Huber, Paul W. & Kantrowitz, Arthur
Partner: UNT Libraries Government Documents Department
open access

Measurements of the Drag and Pressure Distribution on a Body of Revolution Throughout Transition From Subsonic to Supersonic Speeds

Description: Memorandum presenting an investigation of the drag and pressure distribution on a body of revolution of fineness ratio 12 as measured by the free-fall method. Analysis of the results has provided knowledge of the mechanism of the abrupt drag rise which occurs near the speed of sound, and demonstrates that the theoretical method described in a previous report satisfactorily predicts the shape of the measured pressure distributions at low supersonic speeds.
Date: January 16, 1950
Creator: Thompson, Jim Rogers
Partner: UNT Libraries Government Documents Department
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Low-Speed Investigation of the Aerodynamic Loads on the Droop-Nose Flap of a Wing With Leading Edge Swept Back 47.5 Degrees and Having Symmetrical Circular-Arc Airfoil Sections at a Reynolds Number of 4.3 X 10 (Exp 6)

Description: Report presenting an investigation of the pressure distribution on the full-span droop-nose flap of a wing with the leading edge swept back 47.5 degrees and symmetrical circular-arc airfoil sections. Flap pressure distributions were obtained for the base configuration and various deflections of the full-span droop-nose flap and other flap deflection combinations. Information regarding the flow and section characteristics, spanwise loading parameters, center-of-pressure variation, and flap norma… more
Date: January 16, 1950
Creator: Whittle, Edward F., Jr. & Fink, Marvin P.
Partner: UNT Libraries Government Documents Department
open access

Effects on the Snaking Oscillation of the Bell X-1 Airplane of a Trailing-Edge Bulb on the Rudder

Description: From Summary: "A rudder bulb was installed on the trailing edge of the rudder of the Bell X-1 airplane having the 8-percent-thick wing and 6-percent-thick tail. Several flights were made to investigate the effects of the bulb on the snaking oscillation at Mach numbers between 0.75 and 1.0. It was found that the rudder bulb had no noticeable effect on the snaking oscillation over the Mach number range tested."
Date: January 16, 1951
Creator: Drake, Hubert M. & Clagett, Harry P.
Partner: UNT Libraries Government Documents Department
open access

A Lift-Cancellation Technique in Linearized Supersonic-Wing Theory

Description: "A lift-cancellation technique is presented for determining load distributions on thin wings at supersonic speeds. The loading on a wing having a prescribed plan form is expressed as the loading of a known related wing (such as a two-dimensional or triangular wing) minus the loading of an appropriate cancellation wing. The lift-cancellation technique can be used to find the loading on a large variety of wings. Applications to swept wings having curvilinear plan forms and to wings having reentra… more
Date: January 16, 1950
Creator: Mirels, Harold
Partner: UNT Libraries Government Documents Department
open access

Effect of Modifications to Induction System on Altitude Performance of V-1710-93 Engine 3: Use of Parabolic Rotating Guide Vanes and NACA Designed Auxiliary-Stage Inlet Elbow and Interstage Duct

Description: "Bench runs of a modified V-1710-93 engine equipped with a two-stage supercharger, interstage carburetor, aftercooler assembly, and backfire screens have been made at a simulated altitude of 29,000 feet to determine the effect of several induction-system modifications on the engine and supercharger performance. The standard guide vanes on the auxiliary- and engine-stage superchargers were replaced by rotating guide vanes with a parabolic blade profile. The auxiliary-stage inlet elbow and inters… more
Date: January 16, 1947
Creator: Standahar, Ray M. & McCarty, James S.
Partner: UNT Libraries Government Documents Department
open access

[Memorandums on the Subject of D-558 Airplane]

Description: "An investigation of the air-stream fluctuations at the tail of the D-558-1 airplane has been made at high speed for the purpose of determining the vertical region in which the horizontal tail may be placed without becoming subject to tail buffeting. The investigation was made for a range of Mach numbers from 0.775 to 0.907, and a range of vertical positions at the tall to include two proposed horizontal-tail positions. The tests were made at two angles of attack, 0,2 deg. and 4.2 deg., represe… more
Date: January 16, 1947
Creator: Pendley, Robert E.
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Tests of a 1/4-Scale Model of the Naval Aircraft Factory Float-Wing Convoy Interceptor, TED No. NACA 2314

Description: A 1/4 - scale model of the Naval Aircraft Factory float-wing convoy interceptor was tested in the Langley 7-by 10-foot tunnel to determine the longitudinal and lateral stability characteristics. The model was tested in the presence of a ground board to determine the effect of simulating the ground on the longitudinal characteristics.
Date: January 16, 1947
Creator: Wells, Evalyn G. & McKinney, Elizabeth G.
Partner: UNT Libraries Government Documents Department
open access

Tests of a 1/7-Scale Semispan Model of the XB-35 Airplane in the Langley 19-Foot Pressure Tunnel

Description: From Summary: "A 1/7 scale semispan model of the XB-35 airplane was tested in the Langley 10 foot pressure tunnel, primarily for the purpose of investigating the effectiveness of a leading-edge slot for alleviation of stick-fixed longitudinal instability at high angles of attack caused by early tip stalling and a device for relief of stick-free instability caused by elevon up-floating tendencies at high angles of attack. Results indicated that the slot was not adequate to provide the desired im… more
Date: January 16, 1946
Creator: Teplitz, Jerome; Kayten, Gerald G. & Cancro, Patrick A.
Partner: UNT Libraries Government Documents Department
open access

Free-Spinning-Tunnel Tests of a 1/29-Scale Model of the Republic XP-91 Airplane with a Vee Tail Installed

Description: "A spin investigation has been conducted in the Langley 20 -foot free-spinning tunnel on a 1/29 - scale model of the Republic XP-91 airplane with vee tail installed. The effects of control settings and movements upon the effect spin and recovery characteristics of the model were determined for the clean condition (wing tanks removed, landing gear and flaps retracted). The tests were made at a loading simulating that following cruise at altitude and at a time when nearly all fuel was expended" (… more
Date: January 16, 1948
Creator: Snyder, Thomas L.
Partner: UNT Libraries Government Documents Department
open access

Altitude Cooling Investigation of the R-2800-21 Engine in the P-47G Airplane 4 - Engine Cooling-Air Pressure Distribution

Description: "A study of the data obtained in a flight investigation of an R-2800-21 engine in a P-47G airplane was made to determine the effect of the flight variables on the engine cooling-air pressure distribution. The investigation consisted of level flights at altitudes from 5000 to 35,000 feet for the normal range of engine and airplane operation. The data showed that the average engine front pressures ranged from 0.73 to 0.82 of the impact pressure (velocity head). The average engine rear pressures r… more
Date: January 16, 1947
Creator: Kaufman, Samuel J.; Staudt, Robert C. & Valerino, Michael F.
Partner: UNT Libraries Government Documents Department
open access

Effect of Length-Beam Ratio on the Aerodynamic Characteristics of Flying-Boat Hulls without Wing Interference

Description: Contains experimental results of an investigation of the aerodynamic characteristics of a family of flying boat hulls of length beam ratios 6, 9, 12, and 15 without wing interference. The results are compared with those taken on the same family of hulls in the presence of a wing.
Date: January 16, 1948
Creator: Lowry, John G. & Riebe, John M.
Partner: UNT Libraries Government Documents Department
open access

The Effect of Surface Roughness on the Performance of a 23 Degree Conical Diffuser at Subsonic Mach Numbers

Description: Report of an investigation to determine the effect of surface roughness on the performance of a 23 degree conical diffusers with 2:1 ratio of exit to inlet area and a constant-area tail pipe. Information about the pressure survey results, including total-pressure-loss coefficient, diffuser effectiveness, and boundary-layer profiles is provided.
Date: January 16, 1952
Creator: Persh, Jerome
Partner: UNT Libraries Government Documents Department
open access

Effect of Engine and Control Limits on Steady-State and Transient Performance of Turbojet Engine With Variable-Area Exhaust Nozzle

Description: Memorandum presenting steady-state and transient characteristics of the J34-WE-32 turbojet engine with electronic power regulator as obtained in the altitude wind tunnel to determine the effects of engine and control limits on the performance. Limits on the fuel valve and exhaust nozzle area influence any schedule of speed and temperature. Results regarding the effect of limits on operating schedule, effect of altitude on safe operating range, effect of minimum fuel flow settings on transient p… more
Date: January 16, 1953
Creator: Vasu, George & Hinde, William L.
Partner: UNT Libraries Government Documents Department
open access

Low-Lift Buffet Characteristics Obtained From Flight Tests of Unswept Thin Intersecting Surfaces and of Thick 35 Degree Sweptback Surfaces

Description: Report presenting testing of two rocket-propelled research models to determine the effect of the intersection of thin aerodynamic surfaces and the effect of moderate sweepback of thick aerodynamic surfaces on low-lift buffeting. Results regarding trim changes and drag are also provided. It was discovered that low-lift buffeting may be induced at high subsonic speeds by interference due to the intersection of thin aerodynamic surfaces.
Date: January 16, 1953
Creator: Mason, Homer P.
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Distribution of Lift, Drag, and Pitching Moment Between the Wing and Fuselage of a 1/30-Scale Semispan Model of the Bell X-5 Airplane at a Mach Number of 1.24 by the NACA Wing-Flow Method

Description: Report presenting an investigation at a Mach number of 1.24 to determine the distribution of lift, drag, and pitching moment between the wing and fuselage of a scale semispan model of the Bell X-5 airplane. Lift, drag, pitching moments, and wing bending moments were obtained for various angles of attack for 40 through 60 degrees sweptback duralumin wings in the presence of, but detached from, the fuselage.
Date: January 16, 1952
Creator: Silsby, Norman S. & Morris, Garland J.
Partner: UNT Libraries Government Documents Department
open access

The Heat of Combustion of Tetraethyldiborane

Description: "The net heat of combustion of a sample of tetraethyldiborane was found to be 20,400 plus or minus 130 Btu per pound for the reaction of liquid fuel to gaseous carbon dioxide, gaseous water ,and solid boric oxide. The measurements were made in a Parr oxygen bomb calorimeter and the combustion is believed to have been 99 percent complete. A more reasonable value for the net heat of combustion would therefore be 20,600 plus or minus 130 Btu per pound" (p. 1).
Date: January 16, 1957
Creator: Tannenbaum, Stanley
Partner: UNT Libraries Government Documents Department
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Propeller Lift and Thrust Distribution From Wake Surveys of Stagnation Conditions

Description: Paper using the Bernoulli equation for nonsteady flow to derive formulas for propeller lift and thrust distribution in terms of wake-survey measurements of stagnation pressure rise through the propeller. Lift distributions and overall values of thrust from wake survey were compared with direct measurements of those values.
Date: January 16, 1952
Creator: Davidson, Robert E.
Partner: UNT Libraries Government Documents Department
open access

Flight evaluation of the lateral stability and control characteristics of the Convair YF-102 airplane

Description: Report presenting the lateral stability and control characteristics of the Convair YF-102 airplane during flights for the NACA research program. The investigation included gradually increasing sideslips, rudder-fixed aileron rolls, rudder pulses, and trim runs at two different altitudes over the test Mach number range. The lateral handling characteristics appeared satisfactory when viewed in terms of gradually increasing sideslips.
Date: January 16, 1957
Creator: Sisk, Thomas R.; Andrews, William H. & Darville, Robert W.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Control Signals for Variable Ramps of Twin-Duct Side Inlets

Description: Report presenting an investigation in the supersonic wind tunnel to determine the effectiveness of experimental control signals applied to a theoretical inlet throat Mach number control system and normal-shock-position control system for varying the inlet geometry of a twin-duct, side-inlet, fuselage forebody model of a prototype aircraft. These types of control systems have been found to be particularly helpful in supersonic flight. Results regarding inlet stability, control requirements, indi… more
Date: January 16, 1958
Creator: Beheim, Milton A. & Yeager, Richard A.
Partner: UNT Libraries Government Documents Department
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