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 Collection: Technical Report Archive and Image Library
Knock-Limited Performance of Triptane and Xylidines Blended with 28-R Aviation Fuel at High Compression Ratios and Maximum-Economy Spark Setting

Knock-Limited Performance of Triptane and Xylidines Blended with 28-R Aviation Fuel at High Compression Ratios and Maximum-Economy Spark Setting

Date: December 12, 1946
Creator: Held, Louis F. & Pritchard, Ernest I.
Description: An investigation was conducted to evaluate the possibilities of utilizing the high-performance characteristics of triptane and xylidines blended with 28-R fuel in order to increase fuel economy by the use of high compression ratios and maximum-economy spark setting. Full-scale single-cylinder knock tests were run with 20 deg B.T.C. and maximum-economy spark settings at compression ratios of 6.9, 8.0, and 10.0, and with two inlet-air temperatures. The fuels tested consisted of triptane, four triptane and one xylidines blend with 28-R, and 28-R fuel alone. Indicated specific fuel consumption at lean mixtures was decreased approximately 17 percent at a compression ratio of 10.0 and maximum-economy spark setting, as compared to that obtained with a compression ratio of 6.9 and normal spark setting. When compression ratio was increased from 6.9 to 10.0 at an inlet-air temperature of 150 F, normal spark setting, and a fuel-air ratio of 0.065, 55-percent triptane was required with 28-R fuel to maintain the knock-limited brake power level obtained with 28-R fuel at a compression ratio of 6.9. Brake specific fuel consumption was decreased 17.5 percent at a compression ratio of 10.0 relative to that obtained at a compression ratio of 6.9. Approximately similar results were noted at an ...
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of a 0.16-scale model of the X-3 airplane at high subsonic speeds : additional stability and control characteristics and the aerodynamic effects of external stores and ram jets

Wind-tunnel tests of a 0.16-scale model of the X-3 airplane at high subsonic speeds : additional stability and control characteristics and the aerodynamic effects of external stores and ram jets

Date: June 13, 1950
Creator: Cleary, Joseph W & Mellenthin, Jack A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Design of Variable Mach Number Asymmetric Super-Sonic Nozzles by Two Procedures Employing Inclined and Curved Sonic Lines

The Design of Variable Mach Number Asymmetric Super-Sonic Nozzles by Two Procedures Employing Inclined and Curved Sonic Lines

Date: April 11, 1951
Creator: Syvertson, Clarence A. & Savin, Raymond C.
Description: Two theoretical procedures are developed for designing asymmetric supersonic nozzles for which the calculated exit flow is nearly uniform over a range of Mach numbers. One procedure is applicable at Mach numbers less than approximately 3. This approach yields, without iteration, a nozzle for which the calculated exit flow is uniform at two Mach numbers and, with proper design, is nearly uniform at Mach numbers between, slightly above, and slightly below these two. The use of an inclined and curved sonic line is an essential feature of this approach, The second procedure requires iteration and is used far designs at Mach numbers exceeding 3. Although it is not a necessary feature, an inclined and curved sonic line is also used in this procedure. In both approaches the flow field dawn stream of the sonic line is determined using the method of characteristics.
Contributing Partner: UNT Libraries Government Documents Department
A Low-Speed Investigation of a Fuselage-Side Air Inlet for use at Transonic Flight Speeds

A Low-Speed Investigation of a Fuselage-Side Air Inlet for use at Transonic Flight Speeds

Date: April 9, 1947
Creator: Nichols, Mark R. & Goral, Edwin B.
Description: A low-speed investigation in the Langley propeller-research tunnel of annular air inlets designed to avoid compression shocks and attendant boundary-layer separation on the fuselage ahead of the inlets at transonic flight speeds by maintaining substream flow velocities on the fuselage nose was reported in NACA RM No. L6J04. In the present investigation, one of the original annular inlets was converted by the installation of a canopy and a nose-wheel fairing into a twin side inlet in order to study problems involved in applying such an inlet to a fighter-type airplane. Extensive measurements of pressures on the surface of the model and surveys of the internal flow were conducted at angles of attack of 0 degrees, 3 degrees, and 6 degrees over a wide range of inlet-velocity ratio.
Contributing Partner: UNT Libraries Government Documents Department
A transonic wind-tunnel investigation of the effects of nacelle shape and position on the aerodynamic characteristics of two 47 degree sweptback wing-body configurations

A transonic wind-tunnel investigation of the effects of nacelle shape and position on the aerodynamic characteristics of two 47 degree sweptback wing-body configurations

Date: September 2, 1952
Creator: Bielat, Ralph P & Harrison, Daniel E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of Rivet Holes on the Ultimate Strength Developed by 24S-T and Alclad 75S-T Sheet in Incomplete Diagonal Tension

Effect of Rivet Holes on the Ultimate Strength Developed by 24S-T and Alclad 75S-T Sheet in Incomplete Diagonal Tension

Date: January 1, 1943
Creator: Levin, L. Ross & Nelson, David H.
Description: Strength tests were made of a number of 24S-T and Alclad 75S-T aluminum-alloy shear webs to determine the effect of rivet or bolt holes on the shear strength. Data were obtained for webs which approached a condition of pure shear stress as well as for webs with well-developed diagonal tension. The rivet factor, (pitch minus diameter) divided by pitch, was varied from approximately 0.81 to 0.62. These tests indicated that the shear stresses on the gross section were nearly constant for all values of the rivet factor investigated if the other properties of the web were not changed.
Contributing Partner: UNT Libraries Government Documents Department
Exact Calculation of Laminar Boundary Layer in Longitudinal Flow over a Flat Plate with Homogeneous Suction

Exact Calculation of Laminar Boundary Layer in Longitudinal Flow over a Flat Plate with Homogeneous Suction

Date: April 1, 1949
Creator: Iglisch, Rudolf
Description: Lately it has been proposed to reduce the friction drag of a body in a flow for the technically important large Reynolds numbers by the following expedient: the boundary layer, normally turbulent, is artificially kept laminar up to high Reynolds numbers by suction. The reduction in friction drag thus obtained is of the order of magnitude of 60 to 80 percent of the turbulent friction drag, since the latter, for large Reynolds numbers, is several times the laminar friction drag. In considering the idea mentioned one has first to consider whether suction is a possible means of keeping the boundary layer laminar. This question can be answered by a theoretical investigation of the stability of the laminar boundary layer with suction. A knowledge, as accurate as possible, of the velocity distribution in the laminar boundary layer with suction forms the starting point for the stability investigation. E. Schlichting recently gave a survey of the present state of calculation of the laminar boundary layer with suction.
Contributing Partner: UNT Libraries Government Documents Department
Effect of fuselage circumferential inlet location on diffuser-discharge total-pressure profiles at supersonic speeds

Effect of fuselage circumferential inlet location on diffuser-discharge total-pressure profiles at supersonic speeds

Date: October 29, 1956
Creator: Kremzier, Emil J & Wasserbauer, Joseph F
Description: An experimental investigation of the effect of angle of attack and inlet corrected air flow on diffuser-discharge total-pressure profiles of inlets located in various circumferential positions on a fuselage was conducted at supersonic speeds. Results indicated that the diffuser total-pressure profiles for a bottom inlet were least affected by angle of attack on distortion level was obtained with a side inlet. Variation in distortion for top inlets with angle of attack was confined to the supercritical range of inlet operation.
Contributing Partner: UNT Libraries Government Documents Department
Some data on body and jet reaction controls

Some data on body and jet reaction controls

Date: March 4, 1957
Creator: Henning, Allen B; Wineman, Andrew R & Rainey, Robert W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Summary of subsonic-diffuser data

Summary of subsonic-diffuser data

Date: May 18, 1956
Creator: Henry, John R; Wood, Charles C & Wilbur, Stafford W
Description: None
Contributing Partner: UNT Libraries Government Documents Department