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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Memorandum Report
 Collection: National Advisory Committee for Aeronautics Collection
The effect of liquid and ice particles on the erosion of a supercharger-inlet cover and diffuser vanes

The effect of liquid and ice particles on the erosion of a supercharger-inlet cover and diffuser vanes

Date: June 1, 1946
Creator: Rollin, Vern G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: July 6, 1945
Creator: Blair, William K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of Mach number on the aerodynamic characteristics of a single-engine pursuit airplane as determined from tests of a 1/3-scale model

The effect of Mach number on the aerodynamic characteristics of a single-engine pursuit airplane as determined from tests of a 1/3-scale model

Date: May 3, 1945
Creator: Jessen, Henry
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of Maximum Cruise-Power Operation at Ultra-Lean Mixture and Increased Spark Advance on the Mechanical Condition of Cylinder Components

Effect of Maximum Cruise-Power Operation at Ultra-Lean Mixture and Increased Spark Advance on the Mechanical Condition of Cylinder Components

Date: September 1, 1945
Creator: Harris, Herbert B.; Duffy, Robert T. & Erwin, Robert D., Jr.
Description: A continuous 50-hour test was conducted to determine the effect of maximum cruise-power operation at ultra-lean fuel-air mixture and increased spark advance on the mechanical conditions of cylinder components. The test was conducted on a nine-cylinder air-cooled radial engine at the following conditions:brake horsepower, 750; engine speed, 1900 rpm; brake mean effective pressure, 172 pounds per square inch; fuel-air ratio, 0.052; spark advance, 30 deg B.T.C.; and maximum rear-spark-plug-bushing temperature, 400 F. In addition to the data on corrosion and wear, data are presented and briefly discussed on the effect of engine operation at the conditions of this test on economy, knock, preignition, and mixture distribution. Cylinder, piston, and piston-ring wear was small and all cylinder component were in good condition at the conclusion of the 50-hour test except that all exhaust-valve guides were bellmouthed beyond the Army's specified limit and one exhaust-valve face was lightly burned. It is improbable that the light burning in one spot of the valve face would have progressed further because the burn was filled with a hard deposit so that the valve face formed an unbroken seal and the mating seat showed no evidence of burning. The bellmouthing of the exhaust-valve guides is believed ...
Contributing Partner: UNT Libraries Government Documents Department
The effect of modified baffles and auxiliary-cooling ducts on the cooling of a double-row radial engine

The effect of modified baffles and auxiliary-cooling ducts on the cooling of a double-row radial engine

Date: March 1, 1945
Creator: Geisenheyner, Robert M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of NACA injection impeller and ducted head baffles on flight cooling performance of double-row radial engine in four-engine heavy bomber

Effect of NACA injection impeller and ducted head baffles on flight cooling performance of double-row radial engine in four-engine heavy bomber

Date: April 1, 1945
Creator: Vensel, Joseph R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of six aromatic amines on the preignition-limited performance of 28-R aviation fuel in a CFR engine

The effect of six aromatic amines on the preignition-limited performance of 28-R aviation fuel in a CFR engine

Date: May 1, 1945
Creator: Male, Donald W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of some design parameters on ditching characteristics

The effect of some design parameters on ditching characteristics

Date: July 1, 1945
Creator: Dawson, John R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of the performance of a turbosupercharged engine of an exhaust-gas-to-air heat exchanger for thermal ice prevention

Effect of the performance of a turbosupercharged engine of an exhaust-gas-to-air heat exchanger for thermal ice prevention

Date: August 1, 1945
Creator: Look, Bonne C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of the skis on the power-off stability characteristics of a twin-engine cargo airplane

The effect of the skis on the power-off stability characteristics of a twin-engine cargo airplane

Date: June 18, 1945
Creator: Wong, Park Y
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of valve clearance on knock-limited performance and engine cooling

The effect of valve clearance on knock-limited performance and engine cooling

Date: April 1, 1945
Creator: Brown, Kenneth D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of Water-Alcohol Injection and Maximum Economy Spark Advance on Knock-Limited Performance and Fuel Economy of a Large Air-Cooled Cylinder

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

Date: August 1, 1945
Creator: Heinicke, Orville H. & Vandeman, Jack E.
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 constant charge-air flow tests. The tests were conducted at a spark advance of 20 deg B.T.C. and maximum-economy spark advance.
Contributing Partner: UNT Libraries Government Documents Department
Efficiency of a radial-flow exhaust-gas turbosupercharger turbine with a 12.75-inch tip diameter

Efficiency of a radial-flow exhaust-gas turbosupercharger turbine with a 12.75-inch tip diameter

Date: July 1, 1946
Creator: Gabriel, David S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Endurance tests of a 22-inch-diameter pulse-jet engine with a neoprene-coated valve grid

Endurance tests of a 22-inch-diameter pulse-jet engine with a neoprene-coated valve grid

Date: October 1, 1945
Creator: Breisch, John H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An estimate of the effect of engine supercharging on the take-off thrust of a typical helicopter at different altitudes and temperatures

An estimate of the effect of engine supercharging on the take-off thrust of a typical helicopter at different altitudes and temperatures

Date: March 1, 1945
Creator: Voglewede, T J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Estimates of the vertical-tail loads of a Bell P-63A-1 airplane (AAF No. 42-68889) in accelerated rolling maneuvers based on flight tests with two vertical-tail arrangements

Estimates of the vertical-tail loads of a Bell P-63A-1 airplane (AAF No. 42-68889) in accelerated rolling maneuvers based on flight tests with two vertical-tail arrangements

Date: November 1, 1944
Creator: Johnson, Harold I
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Estimation of F-3 and F-4 knock-limited performance ratings for ternary and quaternary blends containing triptane or other high-antiknock aviation-fuel blending agents

Estimation of F-3 and F-4 knock-limited performance ratings for ternary and quaternary blends containing triptane or other high-antiknock aviation-fuel blending agents

Date: January 1, 1948
Creator: Barnett, Henry C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Estimation of the performance and longitudinal stability and control of a lifting-body type of cargo airplane from tests of simplified models

Estimation of the performance and longitudinal stability and control of a lifting-body type of cargo airplane from tests of simplified models

Date: June 1, 1945
Creator: Feigenbaum, D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An evaluation of the knock-limited performance of triptane

An evaluation of the knock-limited performance of triptane

Date: March 1, 1946
Creator: Barnett, Henry C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An Experimental Investigation of Flow Conditions in the Vicinity of an NACA D(Sub S)-Type Cowling

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

Date: August 1, 1946
Creator: Bryant, Rosemary P. & Boswinkle, Robert W.
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.
Contributing Partner: UNT Libraries Government Documents Department
An Experimental Investigation of NACA Submerged-Duct Entrances

An Experimental Investigation of NACA Submerged-Duct Entrances

Date: May 23, 1945
Creator: Frick, Charles W.; Davis, Wallace F.; Randall, Lauros & Mossman, Emmet A.
Description: The results of an investigation of submerged-duct entrances are presented. It is shown that this type of entrance possesses the following characteristics: 1) very high-critical-compressibility speeds throughout the range of high-speed inlet velocity ratios; 2) very low pressure losses for the air entering the duct at all inlet-velocity ratios; and, 3) low external drag. These characteristics are obtained by the proper shaping of the contour of the upstream approach to the submerged inlets and by proper alignment of the duct lip. Design data are presented and the application of these data to a specific high-speed fighter-airplane design is discussed.
Contributing Partner: UNT Libraries Government Documents Department
F-3 and F-4 engine tests of several high-antiknock components of aviation fuel

F-3 and F-4 engine tests of several high-antiknock components of aviation fuel

Date: November 1, 1944
Creator: Genco, Russell S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight and test-stand investigation of high-performance fuels in double-row radial air-cooled engines I : determination of cooling characteristics of flight engine

Flight and test-stand investigation of high-performance fuels in double-row radial air-cooled engines I : determination of cooling characteristics of flight engine

Date: December 1, 1944
Creator: Pragliola, Philip C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight and test-stand investigation of high-performance fuels in double-row radial air-cooled engines II : flight knock data and comparison of fuel knock limits with engine cooling limits in flight

Flight and test-stand investigation of high-performance fuels in double-row radial air-cooled engines II : flight knock data and comparison of fuel knock limits with engine cooling limits in flight

Date: December 1, 1944
Creator: Werner, Milton
Description: None
Contributing Partner: UNT Libraries Government Documents Department