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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Memorandum Report
 Collection: Technical Report Archive and Image Library
Flight tests of the high-speed performance of a P-51B airplane (AAF no. 43-12105)

Flight tests of the high-speed performance of a P-51B airplane (AAF no. 43-12105)

Date: December 18, 1944
Creator: Voglewede, T. J. & Danforth, E. C. D.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Power-off tests of the Northrop N9M-2 tailless airplane in the 40- by 80-foot wind tunnel

Power-off tests of the Northrop N9M-2 tailless airplane in the 40- by 80-foot wind tunnel

Date: December 14, 1944
Creator: Stevens, Victor I., Jr. & Mccormack, Gerald M.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of high-resistance ignition cable on the erosion of spark-plug electrodes

The effect of high-resistance ignition cable on the erosion of spark-plug electrodes

Date: September 1, 1945
Creator: Rodgers, Franklin A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A cooling correlation equation for a double-row radial engine based on the temperature of the exhaust-valve seat

A cooling correlation equation for a double-row radial engine based on the temperature of the exhaust-valve seat

Date: April 1, 1945
Creator: Black, Fred O , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Cooling of a double-row radial engine by water injection to the individual cylinders

Cooling of a double-row radial engine by water injection to the individual cylinders

Date: February 1, 1945
Creator: Friedman, Harold E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of increase in combustion-air inlet temperature from 80 to 130 F on the sea-level performance of a 22-inch-diameter pulse-jet engine

The effect of increase in combustion-air inlet temperature from 80 to 130 F on the sea-level performance of a 22-inch-diameter pulse-jet engine

Date: July 1, 1946
Creator: Hughes, Richard F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Correlation of mixture temperature data obtained from bare intake-manifold thermocouples

Correlation of mixture temperature data obtained from bare intake-manifold thermocouples

Date: January 1, 1946
Creator: White, H. Jack & Gammon, Goldie L
Description: A relatively simple equation has been found to express with fair accuracy, variation in manifold-charge temperature with charge in engine operating conditions. This equation and associated curves have been checked by multi cylinder-engine data, both test stand and flight, over a wide range of operating conditions. Average mixture temperatures, predicted by the equations of this report, agree reasonably well with results within the same range of carburetor-air temperatures from laboratories and test stands other than the NACA.
Contributing Partner: UNT Libraries Government Documents Department
The effect of compression ratio on knock limits of high-performance fuels in a CFR engine I : blends of triptane and 28-R fuel

The effect of compression ratio on knock limits of high-performance fuels in a CFR engine I : blends of triptane and 28-R fuel

Date: February 10, 1945
Creator: Tower, Leonard K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Effect of Compression Ratio on Knock Limits of High-Performance Fuels in a CFR Engine II : Blends of 2,2,3-Trimethylpentane with 28-R

The Effect of Compression Ratio on Knock Limits of High-Performance Fuels in a CFR Engine II : Blends of 2,2,3-Trimethylpentane with 28-R

Date: February 10, 1945
Creator: Tower, Leonard K
Description: The knock-limited performance of blends of 0,50; and 100 percent by volume of 2,2,3-trimethylpentane in 28-R fuel determined with a modified F-4 engine at three sets of conditions varying from severe to mild at each of three compression ratios (6.0, 8.0, and 10.0). A comparison of the knock-limited performance of 2,2,3-trimethylpentane with that of triptane (2,2,3-trimethylbutane) is included. The knock-Limited performance of 2,2,3-trimethylpontane was usually more sensitive to either compression ratio or inlet-air temperature than 28-R fuel, but the ratio of the knock-limited indicated mean effective pressure of a given blend containing 2,2,3-trimethypentane and 28-R to the indicated mean effective pressure of 28-R alone was not greatly affected by compression ratio if the engine operating conditions were mild. Although 2,2,3-trimethylpentane in general had a lower knock-limited performance than triptane, the characteristics of the two fuels were somewhat similar.
Contributing Partner: UNT Libraries Government Documents Department
Effect of engine-operating variables and internal coolants on spark-advance requirements of a liquid-cooled cylinder

Effect of engine-operating variables and internal coolants on spark-advance requirements of a liquid-cooled cylinder

Date: May 1, 1945
Creator: Lietzke, A F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of ethylene dibromide on the knock-limited performance of leaded and nonleaded S reference fuel

The effect of ethylene dibromide on the knock-limited performance of leaded and nonleaded S reference fuel

Date: February 1, 1946
Creator: Niemi, Richard O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of compression ratio on knock limits of high-performance fuels in a CFR engine III : blends of 2,3-dimethylpentane with 28-R

The effect of compression ratio on knock limits of high-performance fuels in a CFR engine III : blends of 2,3-dimethylpentane with 28-R

Date: February 10, 1945
Creator: Tower, Leonard K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of internal coolants on the knock-limited performance of an Allison V-1710-99 engine with a compression ratio of 6.0

Effect of internal coolants on the knock-limited performance of an Allison V-1710-99 engine with a compression ratio of 6.0

Date: June 1, 1945
Creator: Brun, Rinaldo J
Description: None
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
Effect of fuel volatility and mixture temperature on the knocking characteristics of a liquid-cooled single-cylinder test engine

Effect of fuel volatility and mixture temperature on the knocking characteristics of a liquid-cooled single-cylinder test engine

Date: April 1, 1945
Creator: Lietzke, A F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Correlation of the Characteristics of Single-Cylinder and Flight Engines in Tests of High-Performance Fuels in an Air-Cooled Engine I : Cooling Characteristics

Correlation of the Characteristics of Single-Cylinder and Flight Engines in Tests of High-Performance Fuels in an Air-Cooled Engine I : Cooling Characteristics

Date: October 1, 1945
Creator: Wilson, Robert W.; Richard, Paul H. & Brown, Kenneth D.
Description: Variable charge-air flow, cooling-air pressure drop, and fuel-air ration investigations were conducted to determine the cooling characteristics of a full-scale air-cooled single cylinder on a CUE setup. The data are compared with similar data that were available for the same model multicylinder engine tested in flight in a four-engine airplane. The cylinder-head cooling correlations were the same for both the single-cylinder and the flight engine. The cooling correlations for the barrels differed slightly in that the barrel of the single-cylinder engine runs cooler than the barrel of te flight engine for the same head temperatures and engine conditions.
Contributing Partner: UNT Libraries Government Documents Department
Correlation of the characteristics of single-cylinder and flight engines in tests of high-performance fuels in an air-cooled engine II : knock-limited charge-air flow and cylinder temperatures

Correlation of the characteristics of single-cylinder and flight engines in tests of high-performance fuels in an air-cooled engine II : knock-limited charge-air flow and cylinder temperatures

Date: October 1, 1945
Creator: Brown, Kenneth D.; Richard, Paul H. & Wilson, Robert V.
Description: An investigation was conducted to correlate the knock limited performance of flight and single-cylinder engines under a variety of operating conditions.
Contributing Partner: UNT Libraries Government Documents Department
Determination of air-consumption parameters for two radial aircraft engines

Determination of air-consumption parameters for two radial aircraft engines

Date: August 1, 1945
Creator: Howes, William
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of the 0.15-scale powered model of the Fleetwing XBTK-1 airplane : lateral stability and control

Wind-tunnel tests of the 0.15-scale powered model of the Fleetwing XBTK-1 airplane : lateral stability and control

Date: July 1, 1945
Creator: Silvers, H Norman
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Tests of the 0.15-Scale Powered Model of the Fleetwings XBTK-1 Airplane : Longitudinal Stability and Control

Wind-Tunnel Tests of the 0.15-Scale Powered Model of the Fleetwings XBTK-1 Airplane : Longitudinal Stability and Control

Date: May 1, 1945
Creator: Boykin, Rebecca I. & Weil, Joseph
Description: An investigation was made of the static longitudinal stability, and control and stall characteristics of XBTK-1 dive bomber. Results indicate that the longitudinal stability will probably be satisfactory for all contemplated flight conditions at the rear-most CG location with elevator both fixed and free. Power effects were small. Sufficient elevator control will be available to trim in any flight condition above the ground. Increasing the slotted flap deflection above 30 degrees only slightly increased the max. lift coefficient.
Contributing Partner: UNT Libraries Government Documents Department
Two-dimensional wind-tunnel investigation of 0.20-airfoil-chord plain ailerons of different contour on an NACA 65(sub 1)-210 airfoil section

Two-dimensional wind-tunnel investigation of 0.20-airfoil-chord plain ailerons of different contour on an NACA 65(sub 1)-210 airfoil section

Date: December 1, 1945
Creator: Cahill, Jones F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Lift tests of a 0.1536c thick Douglas airfoil section of NACA 7-series type equipped with a lateral-control device for use with a full-span double-slotted flap on the C-74 airplane

Lift tests of a 0.1536c thick Douglas airfoil section of NACA 7-series type equipped with a lateral-control device for use with a full-span double-slotted flap on the C-74 airplane

Date: March 1, 1945
Creator: Rice, Fred J , Jr
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
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
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