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Wind-Tunnel Investigation of the Effects of Spoilers on the Characteristics of a Low-Drag Airfoil Equipped With a 0.25-Chord Slotted Flap

Description: Report discussing the effects of circular-arc spoilers on the section characteristics of an NACA 66,2-216 airfoil with a 0.25-chord slotted flap. Spoilers were tested on the upper surface of the airfoil, on the lower surface, and on both simultaneously. Only the simultaneous placement of spoilers was found to provide satisfactory results as a lateral control device.
Date: July 23, 1945
Creator: Holtzclaw, Ralph W.
Partner: UNT Libraries Government Documents Department
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Flight tests of various tail modifications on the Brewster XSBA-1 airplane 3: measurements of flying qualities with tail configuration 3

Description: Report presenting a series of tests on the Brewster XSBA-1 airplane to determine the effects of various tail modifications. Some of the modifications include variations of the chord of the elevator and rudder while the span and total area of the surfaces are kept constant and variations of the total area of the vertical tail surface. Results regarding the longitudinal stability and control and lateral stability and control are provided.
Date: July 1944
Creator: Crane, H. L. & Reeder, J. P.
Partner: UNT Libraries Government Documents Department
open access

Selection of Oil Coolers to Avoid Congealing

Description: Report presenting a study of oil coolers, especially in regards to three factors: the congealing tendency of the cooler, the power cost chargeable to the installation, and the performance characteristics of the oil cooler in operation at altitude.
Date: July 1943
Creator: Martin, Dennis J.
Partner: UNT Libraries Government Documents Department
open access

Performance Characteristics of Mixed-Flow Impeller and Vaned Diffuser With Several Modifications

Description: Report presenting an investigation of the performance of a mixed-flow impeller and vaned diffuser unit with several modifications in a variable-component supercharger test rig. The investigation covered impeller tip speeds from 800 to 1200 feet per second over the range of air flows from wide-open throttle to incipient surge. The results showed the supercharger to have a peak efficiency of 0.77 and a peak pressure coefficient of 0.61 with the impeller frontal clearance at 0.035 inch.
Date: July 1942
Creator: King, J. Austin & Glodeck, Edward
Partner: UNT Libraries Government Documents Department
open access

Tests of Four Full-Scale Propellers to Determine the Effect of Trailing-Edge Extensions on Propeller Aerodynamic Characteristics

Description: Propellers with trailing-edge extensions were studied to determine aerodynamic characteristics. Trailing-edge extension increased power absorbed by propeller with little loss in efficiency. Power coefficient for maximum efficiency was greater for 20% camber type extension than for 20% straight type extension over range of advance ratio of 1.0 to 2.5 although camber type was less efficient. Efficiency was about the same for cruising and high-speed at a high power coefficient for propeller with e… more
Date: July 1945
Creator: Maynard, Julian D. & Evans, Albert J.
Partner: UNT Libraries Government Documents Department
open access

A Preliminary Theoretical Study of Helicopter-Blade Flutter Involving Dependence Upon Coning Angle and Pitch Setting

Description: "A preliminary analysis has been made of the conditions of stability of free oscillations of a hinged rotor in hovering flight. The case analyzed is a rotor with hinges allowing freedom in flapping and lagging and having a completely reversible cyclic pitch-control system, so that a twisting moment on a blade moves the control stick without hindrance from spring or friction constraint. The principal results of this study are presented in the form of a stability chart" (p. 1).
Date: July 1946
Creator: Coleman, Robert P.
Partner: UNT Libraries Government Documents Department
open access

Heat Transfer Tests of a Steel Cylinder Barrel With Aluminum Fins With Improved Bonding Between Steel Barrel and Aluminum Base

Description: Report presenting testing of a steel cylinder barrel with aluminum fins in order to evaluate the effect of using preformed aluminum fins on a steel barrel or aluminum barrel. Results regarding the heat-transfer tests and physical tests are provided.
Date: July 1940
Creator: Ellerbrock, Herman H., Jr.
Partner: UNT Libraries Government Documents Department
open access

Efficiency of a Radial-Flow Exhaust-Gas Turbosupercharger Turbine With a 12.75-Inch Tip Diameter

Description: Report discussing the effects of various inlet pressures, inlet temperatures, wheel speeds, pressure ratios, and cooling-air flows on the performance of a radial-flow exhaust-gas turbosupercharger turbine with a 12.75-inch tip diameter. Information about efficiency is provided for a given blade-to-jet speed ratio.
Date: July 1946
Creator: Coulter, Earl E.; Larkin, Robert G. & Gabriel, David S.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Methods of Reducing the Temperature Variation Among Cylinders on Air-Cooled Aircraft Engines

Description: Report presenting testing to determine methods for reducing the temperatures of the hot cylinders on air-cooled aircraft engines. A Pratt & Whitney R-1830-43, 14-cylinder engine used for the tests. Results regarding the cooling-air ducts, mixture-enriching tests, additional cooling area, baffle modifications, and an application of the information are provided.
Date: July 1943
Creator: Mueller, William A.
Partner: UNT Libraries Government Documents Department
open access

Measurement of Flying Qualities of a DeHavilland Mosquito F-8 Airplane (AAF No. 43-334960) 2: Longitudinal Stability and Control Characteristics

Description: Report discussing testing to determine the longitudinal stability and control and stalling characteristics of a DeHavilland Mosquito F-8. Special focus is given to the control forces, elevator control, trim changes, and stick fixed and stick free characteristics of the aircraft.
Date: July 1945
Creator: Crane, H. L.; Talmage, D. H. & Gray, W. E., Jr.
Partner: UNT Libraries Government Documents Department
open access

Generalized selection charts for bombers powered by one, two, four, and six 2000-horsepower engines

Description: Report presenting a study of the performance of bombers powered by one, two, four, and six 2000-horsepower engines supercharged to 25,000 feet. The performances are computed and are based on drag coefficients equal to the best obtained on modern airplanes and on weight estimates obtained from modern Army Air Forces airplanes. A chart is provided with the coordinates of power loading and wing loading noted so that all performances can be compared.
Date: July 1942
Creator: Brevoort, M. J.; Stickle, G. W. & Hill, Paul R.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Means for Extending the Range of Several Bombers to 6000 Miles

Description: Report presenting an investigation of means to increase the range of several airplanes to 6000 miles, including the B-17E, B-24D, B-26C, and B-25A. Tank-wing trailers and tank gliders were found to be the most practical ways of increasing range and calculations are provided for determining the proper loading and dimensions.
Date: July 1942
Creator: Ribner, H. S. & Harmon, S. M.
Partner: UNT Libraries Government Documents Department
open access

The Effect of Some Design Parameters on Ditching Characteristics

Description: "The purpose of this report is to provide designers of airplanes with information that will be helpful in obtaining good ditching characteristics in new designs. The results from a number of model tests and report of actual ditchings are used as a basis for which to draw conclusions as to the effect on ditching performance of general arrangement, interior arrangement, fuselage shape, and other design parameters. The characteristics of several types of ditching aids that could be incorporated in… more
Date: July 1945
Creator: Dawson, John R.
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation to Improve the Dynamic Longitudinal Stability and Control-Feel Characteristics of the P-63A-1 Airplane (AAF No. 42-68889) with Closely Balanced Experimental Elevators

Description: Results of flight tests of a control-feel aid presented. This device consisted of a spring and dashpot connected in series between the control stick and airplane structure. The device was tested in combination with an experimental elevator and bobweight which had given unsatisfactory dynamic stability and control-feel characteristics in previous tests. The control-feel aid effected marked improvement in both the control-feel characteristics and the control-feel dynamic longitudinal stability of… more
Date: July 1946
Creator: Johnson, Harold I.
Partner: UNT Libraries Government Documents Department
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Effect of Mach and Reynolds Numbers on the Maximum Lift Coefficient Obtainable in Gradual and Abrupt Stalls of a Pursuit Airplane Equipped With a Low-Drag Wing

Description: Report discussing flight tests on a low-drag wing pursuit airplane to determine the effects of Mach and Reynolds numbers on the maximum lift coefficient obtainable in gradual and abrupt stalls. The obtainable maximum lift coefficient was found to be greatly affected by the Mach and Reynolds numbers in gradual stall. In abrupt stalls, the maximum lift coefficient was affected by the Mach number, but not the Reynolds number.
Date: July 6, 1945
Creator: Spreiter, John R.; Galster, George M. & Blair, William K.
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation to Determine the Relative Magnitude of Vertical and Horizontal Gusts in the Atmosphere

Description: Report presenting an investigation to obtain data on the vertical and horizontal gusts in the atmosphere by reworking accelerometers and airspeed records from past investigations of vertical gusts. The results indicate that the vertical and horizontal gusts are of about equal intensity in the atmosphere.
Date: July 1940
Creator: Donely, Philip
Partner: UNT Libraries Government Documents Department
open access

Wind Tunnel Investigation of the Effect of Jet-Motor Operation Stability

Description: The effects of jet-motor operation on the stability and control characteristics of two fighter-type airplanes as determined by wind-tunnel tests of 1/5-scale models are presented. It is shown that the action of the jets is to cause a small loss in stick-fixed stability which is predictable from known theories.
Date: July 1944
Creator: Davis, Wallace F. & Brown, Sherwood H.
Partner: UNT Libraries Government Documents Department
open access

Water tolerance of aviation gasoline containing xylidines

Description: Report presenting investigations to determine the effect of xylidines on the saturation concentration of water in aviation gasoline. The saturation concentration of water in gasoline containing 0, 1, and 3 percent xylidines was determined using fresh water at two temperatures and sea water at one temperature.
Date: July 1943
Creator: Revilock, Joseph & Olson, Walter T.
Partner: UNT Libraries Government Documents Department
open access

The effect of xylidines on the corrosiveness of aircraft-engine oil

Description: Report presenting testing to determine the effect of xylidines of the corrosiveness of aircraft-engine oil toward engine bearings as part of an investigation on the suitability of xylidines as an antiknock component in aviation gasoline. Results regarding the loss in bearing weight, corrosion losses, temperature characteristics, and types of corrosion are provided.
Date: July 1943
Creator: Meyrowitz, Emanuel & Olson, Walter T.
Partner: UNT Libraries Government Documents Department
open access

Economy of internally cooling only the overheated cylinders of aircraft engines

Description: Report presenting an analysis of cylinder-to-cylinder temperature and mixture distributions of four different aircraft engines to determine the possible economy of automatically supply water or additional fuel to only those cylinders having excessive temperatures. The cooling problem as distinguished from the fuel-knock problem was studied and an analysis limited to those cases in which additional cooling is ordinarily obtained by carburetor enrichment was made.
Date: July 1945
Creator: Biermann, Arnold E.; Miller, George R. & Henneberry, Hugh M.
Partner: UNT Libraries Government Documents Department
open access

Control of Cylinder Temperatures by Thermostatically Operated Internal-Coolant Valves

Description: Report discusses the results of testing conducted to determine the performance of automatic, internal-coolant valves actuated by cylinder temperatures.The performance of the valves with respect to temperature sensitivity, rapidity of response, and hunting characteristics is described. The relative effects on cylinder performance obtained by internally supplying water and additional fuel were also examined.
Date: July 1945
Creator: Biermann, Arnold E.; Henneberry, Hugh M. & Miller, George R.
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics of Several Modifications of a 0.45-Scale Model of the Vertical Tail of the Curtiss XP-62 Airplane

Description: "In the course of an investigation to find a satisfactory vertical tail for the XP-62 airplane, a 0.45-scale vertical tail model on a stub fuselage was tested in the Langley 7- by 10-foot tunnel. This model was fitted with a flat plate to represent the horizontal tail surface. The data are presented herein for their general interest value rather than their application to this particular airplane" (p. 1).
Date: July 1946
Creator: Lowry, John G.; Turner, Thomas R. & Liddell, Robert B.
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation of Factors Affecting the Carburetor Ram and Nacelle Drag of an A-26B Airplane

Description: "Flight tests of an A-26B airplane have been conducted to determine the changes in maximum speed, as affected by changes in carburetor ram and aerodynamic refinement of the nacelles, resulting from the addition of sealed spinners and modification of the charge air system, cowling, and nacelle afterbodies. The changes in nacelle drag resulting from these modifications were measured independently by means of a revolving wake survey rake behind the nacelle and boundary layer rakes on the cowling, … more
Date: July 1946
Creator: Johnston, J. Ford; Klawans, Bernard B. & Danforth, Edward C. B., III
Partner: UNT Libraries Government Documents Department
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