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Aerodynamic Tests of an M-31 Bomb in the 8-Foot High-Speed Tunnel

Description: Report presenting aerodynamic tests of a 300-pound M-31 demolition bomb. Force tests at a range of angles of attack were made at Mach number 0.725, which corresponds to a speed of 810 feet per second at sea level. Results regard the drag, lift, and pitching moment are provided.
Date: August 1942
Creator: Baals, Donald D.
open access

Air-Flow and Performance Characteristics of Engine-Stage Supercharger of a Double-Row Radial Aircraft Engine 2: Effect of Design Variables

Description: Report presenting an investigation to determine the effect of the location of the diffuser vanes with respect to the supercharger outlets and the effect of flow conditions at the impeller inlet on the air-flow distribution in the outlets of the engine-stage supercharger of an 18-cylinder double-row radial aircraft engine. The effect of flow conditions at the impeller inlet was investigated by distorting the flow at the inlet and noting the effect in the supercharger outlets. Results regarding t… more
Date: August 1946
Creator: Baas, Edmund J. & Dugan, Paul D.
open access

Antiknock Effectiveness of Xylidines in Small-Scale Engines

Description: "The data presented in this report are part of a general program to determine the effects of xylidines on the knock-limited performance of currently used aviation fuels" (p. 2).
Date: August 1943
Creator: Branstetter, J. Robert & Meyer, Carl L.
open access

Attainment of a Straight-Line Trajectory for a Preset Guided Missile With Special Reference to Effect of Wind or Target Motion

Description: Report discusses the results of a study "of the requirements for the attainment of a straight-line trajectory for a preset guided missile in the presence of wind or target motion" (from Summary). Information about the straight-line trajectory, position of the launching airplane, straight-line collision course, and arrangement of the autopilot in the missile is provided. Recommendations are also made about the creation of a bombsight mounting for the pilot of the launching airplane in order to a… more
Date: August 1945
Creator: Ribner, Herbert S.
open access

Correlation of Wind-Tunnel Predictions With Flight Tests of a Twin-Engine Patrol Airplane 2: Lateral- and Directional-Stability and Control Characteristics

Description: "The lateral- and directional-stability and -control characteristics of a twin-engine patrol airplane as predicted from the results of wind-tunnel tests of a powered model and as measured in flight are compared in this report. The predictions from wind-tunnel-test data were in good agreement with the flight-test results. The results show that such predicted flying-qualities characteristics are sufficiently accurate to indicate the unsatisfactory lateral- and directional-stability and -control c… more
Date: August 30, 1945
Creator: Delany, Noel K. & Kauffman, William M.
open access

Determination of Air-Consumption Parameters for Two Radial Aircraft Engines

Description: "Air-consumption data from calibrations of two radial aircraft engines were analyzed to show the relation of engine air consumption to its primary influencing factors: intake-manifold pressure, exhaust back pressure, intake-manifold temperature, and engine speed. The analysis of the test data from these two engines led to the establishment of a relation of variables upon which the design of automatic metering controls can be based. The data obtained from one engine indicate that the air-consump… more
Date: August 1945
Creator: Shames, Sidney J. & Howes, William
open access

Ditching Tests With a 1/12-Size Model of the Army B-26 Airplane in NACA Tank Number 2 and on an Outdoor Catapult

Description: Report presenting tests made with a dynamic model of the Army B-26 airplane to determine its behavior when landed on water. Results regarding the general behavior, effect of flaps, effect of landing attitude and speed, tests with undamaged model, tests with simulated damage, tests with propellers, vertical decelerations, and effect of weight are provided.
Date: August 1944
Creator: Fisher, Lloyd J. & Steiner, Margaret F.
open access

Effect of the Performance of a Turbosupercharged Engine of an Exhaust-Gas-to-Air Heat Exchanger for Thermal Ice Prevention

Description: This report presents the results of a flight investigation to determine the effect on the performance of a turbosupercharged engine of an exhaust-gas-to-air heat exchanger installed between the engine-exhaust collector ring and the turbosupercharger. The background, results, and discussion of the investigation are described.
Date: August 23, 1945
Creator: Look, Bonne C.
open access

Effect of Water-Alcohol Injection and Maximum Economy Spark Advance on Knock-Limited Performance and Fuel Economy of a Large Air-Cooled Cylinder

Description: An investigation was conducted to determine the effect of a coolant solution of 25 percent ethyl alcohol, 25 percent methyl alcohol, and 50 percent water by volume and maximum-economy spark advance on knock-limited performance and fuel economy of a large air-cooled cylinder. The knock-limited performance of the cylinder at engine speeds of 2100 and 2500 rpm was determined for coolant-fuel ratios of 0.0, 0.2, and 0.4. The effect of water-alcohol injection on fuel economy was determined in consta… more
Date: August 12, 1945
Creator: Heinicke, Orville H. & Vandeman, Jack E.
open access

The effect of xylidines on the load-carrying capacity of an aircraft-engine oil 1

Description: Report presenting testing to determine the effect of xylidines on the load-carrying capacity of aircraft-engine oil in several test devices. Lubricating oil and lubricating oil with xylidines added was tested in four different testing machines. In all of the experiments, adding the xylidines made the oil a poorer lubricant in the boundary region of lubrication, where metal-to-metal contact occurs.
Date: August 1943
Creator: Spurr, Robert A. & Olson, Walter T.
open access

The Effect of Xylidines on the Stability of an Aircraft-Engine Lubricating Oil

Description: Report presenting tests to determine the effect of xylidines on the stability of an aircraft-engine lubricating oil. The Indiana oxidation test and measurements of the oxygen absorption rate of the oil samples were performed on Navy 1120 oil, Navy 1120 oil plus 0.5 percent by weight of xylidines, and Navy 1120 oil used in piston-ring-sticking tests both with and without xylidines. Results regarding the Indiana oxidation test, the Davis oxidation test, the automatic oil-oxidation apparatus, and … more
Date: August 1943
Creator: Olson, Walter T. & Meyrowitz, Emanuel
open access

Elimination of rumble from the cooling ducts of a single-engine pursuit airplane

Description: Report presenting a full-size single-engine pursuit airplane, with wing tips cut off, tested in the 16-foot wind tunnel. The purpose was to find means for eliminating an extreme rumble which occurred at high speeds when the radiator air-duct-exit openings were small. Results regarding rumble, cooling air, and drag are provided.
Date: August 1943
Creator: Matthews, Howard F.
open access

An Experimental Investigation of Flow Conditions in the Vicinity of an NACA D(Sub S)-Type Cowling

Description: Data are presented of the flow conditions in the vicinity of an NACA D sub S -type cowling. Tests were made of a 1/2 scale-nacelle model at inlet-velocity ratios ranging from 0.23 to 1.02 and angles of attack from 6 deg to 10 deg. The velocity and direction of flow in the vertical plane of symmetry of the cowling were determined from orifices and tufts installed on a board aligned with the flow. Diagrams showing velocity ratio contours and lines of constant flow angles are given.
Date: August 1946
Creator: Bryant, Rosemary P. & Boswinkle, Robert W., Jr.
open access

Flight and Test-Stand Investigation of High-Performance Fuels in Modified Double-Row Radial Air-Cooled Engines 3: Knock-Limited Performance of 33-R as Compared with a Triptane Blend and 28-R in Flight

Description: "A comparison has been made in flight of the antiknock characteristics of 33-R fuel with that of 28-R and a triptane blend. The knock-limited performance of the three fuels - 33-R, a blend of 80 percent 28-R plus 20 percent triptane (leaded to 4.5 ml TEL/gal), and 28-R - was investigated in two modified 14-cylinder double-row radial air-cooled engines. Tests were conducted on the engines as installed in the left inboard nacelle of an airplane. A carburetor-air temperature of approximately 85 de… more
Date: August 1945
Creator: Blackman, Calvin C. & White, H. Jack
open access

Flutter tests of modified SB2U model in 16-foot tunnel

Description: Report presenting testing of the flutter characteristics of the SB2U model conducted after the model had been modified to lower its flutter speed. The model was tested to destruction and the flutter speed was measured throughout.
Date: August 1943
Creator: Theodorsen, Theodore; Coleman, R. P. & Smith, N. H.
open access

Gasoline-water distribution coefficients of 27 aromatic amines

Description: Report presenting an investigation of the suitability of 27 aromatic amines for overwater storage of their gasoline blends. The program is also meant to determine the antiknock effectiveness and low-temperature solubility in gasoline.
Date: August 1944
Creator: Olson, Walter T.; Tischler, Adelbert O. & Goodman, Irving A.
open access

Generalized selection charts for bombers powered by one, two, four, and six 3000-horsepower engines 1: capacity and economy

Description: Supplement using data from a previous report to show the cargo that can be carried at various ranges, pounds of cargo that can be carried per pound of fuel, and other graphs to simplify the problem of determining which cargo can be carried at any range. The assumptions, parameters, and equations from the original report are carried over in the supplement.
Date: August 1942
Creator: Brevoort, Maurice J.; Stickle, George W. & Hill, Paul R.
open access

Generalized selection charts for bombers powered by two, four, and six 3000-horsepower engines

Description: Report presenting a study of the performance of bombers powered by two, four, and six 3000-horsepower engines supercharged to 35,000 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: August 1942
Creator: Brevoort, Maurice J.; Stickle, George W. & Hill, Paul R.
open access

Heat-Transfer Tests of a Steel Cylinder Barrel With Aluminum Fins

Description: Report presenting tests conducted on a steel cylinder barrel with aluminum fins in order to determine the heat-transfer coefficients of the cylinder and the excellence of the bond between the steel barrel and the aluminum fins. Results regarding the heat-transfer tests and physical tests are provided.
Date: August 1939
Creator: Ellerbrock, Herman H., Jr.
open access

Heat-Transfer Tests of Two Steel Cylinder Barrels With Aluminum Fins Manufactured by Factory Production Method

Description: Report presenting testing of two engine cylinder barrels with aluminum fins. The primary purpose was to determine the heat-transfer coefficients and the excellence of the bonds between the aluminum fins and the aluminum base and between the aluminum base and the steel of the two barrels when manufactured by a large-volume production method.
Date: August 1940
Creator: Ellerbrock, Herman H., Jr.
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