UNT Libraries Government Documents Department - 51 Matching Results

Search Results

Results: 1 - 24 next
open access

Aerodynamic and Hydrodynamic Tests of a Family of Models of Flying-Boat Hulls Derived From a Streamline Body: NACA Model 84 Series

Description: Report presenting a series of related flying-boat hull forms with various combinations of aerodynamic and hydrodynamic requirements that were tested in an NACA tank and high-speed tunnel. Effects explored included varying the height of the bow, varying the height of the stern, increasing the angle of dead rise at the bow, decreasing the angle of dead rise on the afterbody, increasing the depth of step, increasing the angle of afterbody keel, adding chine flare, adding a third planing surface, a… more
Date: September 1943
Creator: Parkinson, John B.; Olson, Roland E.; Draley, Eugene C. & Luoma, Arvo A.
Item Type: Refine your search to only Report
open access

Air-consumption parameters for automatic mixture control of aircraft engines

Description: From Introduction: "The purpose of this analysis was to investigate the use of function of intake-manifold temperature and pressure, exhaust back pressure, and engine speed in place of a ventri as a means of measuring engine air consumption and to determine if this function is suitable for automatic mixture control."
Date: September 1944
Creator: Shames, Sidney J.
Item Type: Refine your search to only Report
open access

Analysis of factors affecting net lift increment attainable with trailing-edge split flaps on tailless airplanes

Description: From Introduction: "The lift increments of different flap arrangements were determined by the method of reference 1 with a simple chord correction factor being applied. This procedure is somewhat similar in basic principles to the method of reference 2. The accuracy of the present method was determined by calculating by means of this method the lift and moment increments of flaps on 10 different finite wing-flap combinations for which wind-tunnel data were available."
Date: September 1944
Creator: Maggin, Bernard
Item Type: Refine your search to only Report
open access

Charts for Determining Jet-Boundary Corrections for Complete Models in 7- by 10-Foot Closed Rectangular Wind Tunnels

Description: Report presenting calculations of numerical values of the jet-boundary corrections to the angle of attack and the induced-drag, rolling-moment, and yawing-moment coefficients for complete airplane or wing models in 7- by 10-foot closed rectangular wind tunnels. The results showed that the wing area was the most important variable, as has usually been assumed in previous calculations. When the corrections were based on wing area, the effect of most of the other variables was negligible.
Date: September 1945
Creator: Gillis, Clarence L.; Polhamus, Edward C. & Gray, Joseph L., Jr.
Item Type: Refine your search to only Report
open access

Critical Speeds and Profile Drag of the Inboard Sections of a Conventional Propeller

Description: Report presenting the section critical speeds and profile drags of the shank and hub sections of a propeller used on a current liquid-cooled-engine pursuit type of airplane. Results indicated that serious adverse compressibility effects can be expected at speeds of about 400 miles per hour. Suitable fairings for shank and hub sections were found to be necessary for maximum propulsive efficiency.
Date: September 1941
Creator: Luoma, Arvo A.
Item Type: Refine your search to only Report
open access

The design of the optimum hull for a large long-range flying boat

Description: Report presenting some principles for designing the optimum hull for a large long-range flying boat in order to suit the requirements of minimum drag, seaworthiness, and ability to take off and land at all operational gross weights. The principles include the use of moderate gross-load coefficients, ample forebody lengths, and deep steps and the close adherence of the form to that of a streamline body of revolution with a moderate fineness ratio.
Date: September 1944
Creator: Parkinson, John B.
Item Type: Refine your search to only Report
open access

Dynamic stress calculations for two airplanes in various gusts

Description: Report presenting a series of calculations made to determine the probable dynamic wing stress of two large airplanes in atmospheric gusts. The results indicate that in both isolated and repeated gusts of probable occurrence, the dynamic overstress is about 10 percent when referred to the present static design standard.
Date: September 1941
Creator: Pierce, Harold B.
Item Type: Refine your search to only Report
open access

Effect of Aromatics and Spark Advance on Thermal Efficiency

Description: Report presenting an analysis of experimental and theoretical data, which indicates that critical evaluation of fuel performance, especially economy, must be made in the engine. Data show that heating value is, from the aspect of fuel economy, not so important an aviation-fuel specification as believed. The knock ratings of fuels are affected by spark advance.
Date: September 1942
Creator: Gilbert, Mitchell
Item Type: Refine your search to only Report
open access

The Effect of Carburetor-Air Temperature on the Cooling Characteristics of a Typical Air-Cooled Engine Cylinder

Description: Report presenting an investigation that was conducted to determine the effect of carburetor dry-air temperature on the cooling characteristics of a typical full-scale air-cooled engine cylinder mounted on a single-cylinder crankcase.
Date: September 1945
Creator: Neustein, Joseph; Sens, William H. & Buckner, Howard A., Jr.
Item Type: Refine your search to only Report
open access

The Effect of Carburetor Throttle Settings on the Velocity Distribution at the Outlet of a Vaned and Vaneless Supercharger Inlet Elbow

Description: Report presenting a study to determine the effect of a carburetor and an inlet elbow on the flow at the supercharger impeller inlet. Tests were conducted on a commercial vaned supercharger inlet-elbow assembly to determine the effect on the velocity distribution at the elbow outlet. Results indicated that the velocity profile obtained at the outlet of the vaneless elbow was better than that with the vaned elbow at all throttle settings.
Date: September 1945
Creator: Guentert, Donald C. & Baas, Edmund J.
Item Type: Refine your search to only Report
open access

The Effect of Cowling Shape on the Stability Characteristics of an Airplane

Description: "Three widely different nose shapes were tested on a fuselage alone and on a complete model in the UACA stability tunnel to investigate the effect of cowling shape on stability characteristics. The results are presented in the form of charts which show the variation in the aerodynamic characteristics with the three nose shapes for the propeller-removed condition over a wide range of angles of attack and yaw. The results of the investigation indicated that large changes in the cowling shape prod… more
Date: September 1942
Creator: Donlan, C. J. & Letko, W.
Item Type: Refine your search to only Report
open access

Effect of Fuel Volatility on Performance of a Wright R-2600-8 Engine as Influenced by Mixture Distribution

Description: Report presenting an investigation to determine the effect of fuel volatility on engine power and economy as influenced by mixture distribution. Tests of four fuels of different volatility were conducted on a Wright R-2600-8 engine at desired cruising power, maximum cruising power, normal rated power, and takeoff power.
Date: September 1944
Creator: White, H. Jack & Engelman, Helmuth W.
Item Type: Refine your search to only Report
open access

Effect of Ground on Characteristics of Model of a Low-Wing Airplane With Full-Span Slotted Flap With and Without Power

Description: Report presenting ground-effect tests made in the LMAL 7- by 10-foot tunnel of a model of a low-wing, pursuit-type airplane equipped with a full-span 25-percent-chord slotted flap. Testing occurred at different heights and power conditions, and two stabilizer and elevator settings were used at each condition. Results indicated that the elevator deflection required for landing in a three-point attitude with the full-span slotted flap was considerably greater than that required with a partial-spa… more
Date: September 1942
Creator: Recant, I. G. & Wallace, A. R.
Item Type: Refine your search to only Report
open access

The Effect of Inlet Temperature and Pressure on the Efficiency of Single-Stage Impulse Turbine Having a 13.2-Inch Pitch-Line Diameter Wheel

Description: From Summary: "Efficiency tests have been conducted on a single-stage impulse turbine having a 13.2-inch pitch-line diameter wheel and a cast nozzle diaphragm over a range of turbine speeds from 3000 to 17,000 rpm, pressure ratios from 1.5 to 5.0, inlet total temperatures from 1200 deg to 2000 deg R, and inlet total pressures from 18 to 59 inches of mercury absolute. The effect of inlet temperature and pressure on turbine efficiency for constant pressure ration and blade-to-jet speed ration is … more
Date: September 1945
Creator: Chanes, Ernest R. & Carman, L. Robert
Item Type: Refine your search to only Report
open access

Effect of several methods of increasing knock-limited power on cylinder temperatures

Description: Report presenting a study to determine the effect of several methods of increasing the knock-limited power on critical cylinder temperatures. The knock-limited indicated horsepower and cylinder temperatures were determined for a Wright R-2600-8 cylinder under specified operating conditions. The most satisfactory method of increasing knock limited power was found to be internal cooling with water and the least satisfacotry was increasing the engine speed.
Date: September 1944
Creator: Cook, Harvey A.; Vandeman, Jack E. & Brown, Kenneth D.
Item Type: Refine your search to only Report
open access

Fatigue Tests of Riveted Joints : Progress Report of Tests of 17S-T and 53S-T Joints

Description: Report presenting the fatigue data obtained at the Aluminum Research Laboratories from tests of various types of 17S-T and 53S-T specimens. The specimens were large enough to represent actual service conditions, but the repetition of loading was more rapid than would occur in ordinary service.
Date: September 1944
Creator: Hartmann, E. C.; Lyst, J. O. & Andrews, H. J.
Item Type: Refine your search to only Report
open access

A Flight Investigation of the Effect of Surface Roughness on Wing Profile Drag With Transition Fixed

Description: Report presenting a flight investigation made on a wing section of a P-47D airplane to determine the effect of roughness on wing profile drag with transition fixed far forward. Surveys of the wake were made for two surface conditions with transition fixed by a thread at 5 percent chord back of the leading edge on the upper and lower surfaces. Below the Mach number at which shock occurred, variations in Mach number of as much as 0.16 appeared to have no appreciable effect on the section profile-… more
Date: September 1944
Creator: Zalovcik, John A. & Wood, Clotaire
Item Type: Refine your search to only Report
open access

Foaming of Aircraft-Engine Oils as a Problem in Colloid Chemistry - 1

Description: Report presenting an investigation conducted on the foaming characteristics of representative aircraft-engine lubricants in order to arrive at an adequate theory of the foaming of such oils. Methods of measuring foaming are compared and analyzed for their significant factors.
Date: September 1944
Creator: McBain, J. W.; Ross, S.; Brady, A. P.; Robinson, J. V.; Abrams, I. M.; Thorburn, R. C. et al.
Item Type: Refine your search to only Report
open access

General porpoising tests on flying-boat-hull models

Description: Report presenting evidence in support of the propriety of substituting a general porpoising test of flying boat hull models in place of the usual specific test. The results of a general test are presented and compared with the results of a specific test of the same model.
Date: September 1943
Creator: Locke, F. W. S., Jr.
Item Type: Refine your search to only Report
open access

High-Altitude Cooling 1: Resume of the Cooling Problem

Description: Report presenting a paper in a series about the cooling of aircraft-engine installations with special reference to the difficulties of cooling at high altitudes. This particular paper discusses the properties of NACA standard air and Army summer air, with corresponding stagnation conditions for a range of flight speed, as summarized in tables and figures.
Date: September 1944
Creator: Silverstein, Abe
Item Type: Refine your search to only Report
open access

High-Altitude Cooling 2: Air-Cooled Engines

Description: Report presenting the heat-transfer theory for air-cooled engines and an analysis of the cooling pressure drop for the case in which the pressure drop is an appreciable fraction of the absolute pressure. A chart is given for the simple determination of the cooling pressure drop predicted on the basis of the usual type of sea-level cooling-correlation tests.
Date: September 1944
Creator: Williams, David T.
Item Type: Refine your search to only Report
open access

High-Altitude Cooling 3: Radiators

Description: Report presenting a detailed analysis to take account of the high cooling-air velocity occurring in high-altitude radiators. Methods are developed for determining the heat-transfer rate, the pressure drop, and the drag power. Radiator performance charts based on the analysis are presented for a wide range of the design variables.
Date: September 1944
Creator: Nielsen, Jack N.
Item Type: Refine your search to only Report
open access

High-Altitude Cooling 4: Intercoolers

Description: "The variation of intercooling requirements with altitude is discussed and the corresponding effects on intercooler design are shown. A discussion is also given of the relations among the various design parameters and of the ranges of choice in design. The important effects of the various factors on intercooler proportions are illustrated with charts for the Harrison copper cross-flow intercooler" (p. 1).
Date: September 1944
Creator: Rubert, K. F.
Item Type: Refine your search to only Report
Back to Top of Screen