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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Memorandum Report
 Collection: Technical Report Archive and Image Library
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
Flight variables affecting fuel-vapor loss from a fuel tank

Flight variables affecting fuel-vapor loss from a fuel tank

Date: December 1, 1944
Creator: Black, Dugald O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Knock-limited performance of blends of AN-F-28 fuel containing 2 percent aromatic amines IV

Knock-limited performance of blends of AN-F-28 fuel containing 2 percent aromatic amines IV

Date: December 1, 1944
Creator: Tower, Leonard K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Measurement of flying qualities of a Douglas A-26B airplane (AAF No. 41-39120) I : longitudinal stability and control characteristics

Measurement of flying qualities of a Douglas A-26B airplane (AAF No. 41-39120) I : longitudinal stability and control characteristics

Date: December 1, 1944
Creator: Hoover, H H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of a thermal ice-prevention system for a wing leading-edge landing-light installation

Tests of a thermal ice-prevention system for a wing leading-edge landing-light installation

Date: December 11, 1944
Creator: Hillendahl, Wesley H
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
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
High-speed wind-tunnel tests of semispan horizontal tails with fabric-covered and metal-covered elevators for a bomber airplane

High-speed wind-tunnel tests of semispan horizontal tails with fabric-covered and metal-covered elevators for a bomber airplane

Date: December 18, 1944
Creator: Nelson, Warren H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind Tunnel Investigation of the Effects of Slot Shape and Flap Location on the Characteristics of a Low-Drag Airfoil Equipped with a 0.25-Chord Slotted Flap

Wind Tunnel Investigation of the Effects of Slot Shape and Flap Location on the Characteristics of a Low-Drag Airfoil Equipped with a 0.25-Chord Slotted Flap

Date: December 28, 1944
Creator: Weisman, Yale & Holtzclaw, Ralph W.
Description: Tests were conducted at dynamic pressure of 50 lb per square foot with lift drag and pitch moment measurements throughout useful angle of attack range for constant flap deflection and position of a low-drag airfoil. Two slots were investigated and practical flap paths were selected for each Slot shape had a negligible effect on the maximum lift coefficient flap deflected, the rounded-entry slot had lower profile drag.
Contributing Partner: UNT Libraries Government Documents Department
Correlation of engine-cooling data

Correlation of engine-cooling data

Date: January 1, 1945
Creator: Brevoort, Maurice J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Langley full-scale-tunnel stability and control tests of the Bell YP-59A airplane

Langley full-scale-tunnel stability and control tests of the Bell YP-59A airplane

Date: January 1, 1945
Creator: Brewer, Gerald W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Measurement of flying qualities of a Douglas A-26B airplane (AAF No. 41-39120) II : lateral and directional stability and control characteristics

Measurement of flying qualities of a Douglas A-26B airplane (AAF No. 41-39120) II : lateral and directional stability and control characteristics

Date: January 1, 1945
Creator: Hoover, H H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Measurement of flying qualities of a Douglas A-26B airplane (AAF No. 41-39120) III : stalling characteristics

Measurement of flying qualities of a Douglas A-26B airplane (AAF No. 41-39120) III : stalling characteristics

Date: January 1, 1945
Creator: Hoover, H H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Measurement of individual aileron hinge moments and aileron control characteristics of a P-40F airplane

Measurement of individual aileron hinge moments and aileron control characteristics of a P-40F airplane

Date: January 1, 1945
Creator: Goranson, R Fabian
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Tests of a 1/5-Scale Semispan Model of the Republic XF-12 Horizontal Tail Surface

Wind-Tunnel Tests of a 1/5-Scale Semispan Model of the Republic XF-12 Horizontal Tail Surface

Date: January 1, 1945
Creator: Denaci, H. G.
Description: Wind-tunnel tests of a 1/5-scale semispan model of the Republic XF-12 horizontal tail surface equipped with an internally balanced elevator were conducted in the 6- by 6-foot test section of the Langley stability tunnel. The tests included measurements of the aerodynamic characteristics of the horizontal tail with and without a beveled trailing edge and also included measurements of the tab characteristics. The variation of the aerodynamic characteristics with boundary-layer conditions and leakage in the internal-balance chambers, measurements of the boundary-layer displacement thickness near the elevator hinge axis, and pressure distributions at the mean geometric chord were also obtained. The results showed that the hinge-moment characteristics of the elevator were critical to boundary-layer conditions and internal-balance leakage. Increasing the boundary-layer displacement thickness by use of roughness strips reduced the rate of change of elevator hinge moments with tab deflection by about 20 percent. The present horizontal tail appears to be unsatisfactory for longitudinal stability with power on, however, an increase in horizontal-tail lift effectiveness should correct this difficulty. The maneuvering stick force per unit acceleration will be extremely critical to minor variations of the elevator hinge moments if the elevator is linked directly to the stick.
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Tests of a 1/6-Scale Model of Republic XF-12 Vertical Tail Incorporating a De-Icing Air Duct

Wind-Tunnel Tests of a 1/6-Scale Model of Republic XF-12 Vertical Tail Incorporating a De-Icing Air Duct

Date: January 1, 1945
Creator: MacLachlan, Robert & Miller, Sadie M.
Description: A 1/6-scale model of the Republic XF-12 vertical tail with stub fuselage, stub horizontal tail, and a de-icing air duct was tested in the Langley stability tunnel. The investigation consisted of a study of the effects of the duct, with and without air flow, on the aerodynamic characteristics of the model. The model tested was a revision of a model previously tested in the Langley stability tunnel. The revised model differed from the original model in that it incorporated a de-icing air duct, included a dorsal fin, and had a larger stub fuselage. A comparison of data obtained form tests of the original and revised models was made. The results of the investigation indicated that the air duct had very little effect on the aerodynamic characteristics of the model. A small change occurred in the variation of rudder hinge-moment coefficient with angle of attack but it is believed that this change can be corrected by a properly applied spring tab.
Contributing Partner: UNT Libraries Government Documents Department
An investigation of a thermal ice-prevention system for a C-46 cargo airplane V : effect of thermal system on airplane cruise performance

An investigation of a thermal ice-prevention system for a C-46 cargo airplane V : effect of thermal system on airplane cruise performance

Date: January 13, 1945
Creator: Selna, James
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
Flight measurements of the flying qualities of an F6F-3 airplane (BuAer No. 04776) I : longitudinal stability and control

Flight measurements of the flying qualities of an F6F-3 airplane (BuAer No. 04776) I : longitudinal stability and control

Date: February 1, 1945
Creator: Reeder, John P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight measurements of the flying qualities of an F6F-3 airplane (BuAer No. 04776) II : lateral and directional stability and control

Flight measurements of the flying qualities of an F6F-3 airplane (BuAer No. 04776) II : lateral and directional stability and control

Date: February 1, 1945
Creator: Reeder, John P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight measurements of the flying qualities of an F6F-3 airplane (BuAer No. 04776) III : stalling characteristics

Flight measurements of the flying qualities of an F6F-3 airplane (BuAer No. 04776) III : stalling characteristics

Date: February 1, 1945
Creator: Reeder, John P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tests of a 1/14-scale powered model of the XB-36 airplane in the Langley 19-foot pressure tunnel I : stalling characteristics and aileron effectiveness of several wing and flap arrangements

Tests of a 1/14-scale powered model of the XB-36 airplane in the Langley 19-foot pressure tunnel I : stalling characteristics and aileron effectiveness of several wing and flap arrangements

Date: February 1, 1945
Creator: Sivells, James C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Knock-limited blending characteristics of benzene, toluene, mixed xylenes, and cumene in an air-cooled cylinder

Knock-limited blending characteristics of benzene, toluene, mixed xylenes, and cumene in an air-cooled cylinder

Date: February 3, 1945
Creator: Breitwieser, Roland
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 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