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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Year: 1957
 Collection: Technical Report Archive and Image Library
Transonic Flutter Investigation of an All-movable Horizontal Tail for a Fighter Airplane

Transonic Flutter Investigation of an All-movable Horizontal Tail for a Fighter Airplane

Date: January 14, 1957
Creator: Abbott, F. T., Jr. & Land, N. S.
Description: Transonic flutter of all-movable horizontal tail - bending & pitching moments.
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation of a liquid hydrogen fuel system

Flight investigation of a liquid hydrogen fuel system

Date: August 19, 1957
Creator: Acker, L. W.; Christenson, H. H.; Gough, W. V. & Mulholland, D. R.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Accelerations in fighter-airplane crashes

Accelerations in fighter-airplane crashes

Date: November 4, 1957
Creator: Acker, Loren W; Black, Duglad O & Moser, Jacob C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of downwash, sidewash, and Mach number distribution behind a rectangular wing at a Mach number of 2.41

Investigation of downwash, sidewash, and Mach number distribution behind a rectangular wing at a Mach number of 2.41

Date: January 1, 1957
Creator: Adamson, David & Boatright, William B
Description: An investigation of the nature of the flow field behind a rectangular wing of circular arc cross section has been conducted in the Langley 9-inch supersonic tunnel. Pitot- and static-pressure surveys covering a region of flow behind the wing have been made together with detailed pitot surveys throughout the region of the wake. In addition, the flow direction has been measured by means of a weathercocking vane. Theoretical calculations have been made to obtain the variation of both downwash and sidewash with angle of attack by using the superposition method of Lagerstrom, Graham, and Grosslight. In addition, the effect of wing thickness on the sidewash with the wing at 0 degree angle of attack has been evaluated.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of horizontal-tail loads in pitching maneuvers on a flexible swept-wing jet bomber

Analysis of horizontal-tail loads in pitching maneuvers on a flexible swept-wing jet bomber

Date: December 1, 1957
Creator: Aiken, William S , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Horizontal-tail parameters as determined from flight-test tail loads on a flexible swept-wing jet bomber

Horizontal-tail parameters as determined from flight-test tail loads on a flexible swept-wing jet bomber

Date: January 17, 1957
Creator: Aiken, William S , Jr & Fisher, Raymond A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental static aerodynamic forces and moments at high subsonic speeds on a canard missile during simulated launching from the midsemispan location of a 45 deg sweptback wing-fuselage-pylon combination at zero sideslip

Experimental static aerodynamic forces and moments at high subsonic speeds on a canard missile during simulated launching from the midsemispan location of a 45 deg sweptback wing-fuselage-pylon combination at zero sideslip

Date: January 14, 1957
Creator: Alford, W. J., Jr. & King, T. J., Jr.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of flow fields at zero sideslip near swept- and unswept-wing-fuselage combinations at low speed

Experimental investigation of flow fields at zero sideslip near swept- and unswept-wing-fuselage combinations at low speed

Date: January 18, 1957
Creator: Alford, William J & King, Thomas J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental static aerodynamic forces and moments at high subsonic speeds on a missile model during simulated launching from unswept-, sweptback and modified-delta-wing-fuselage combinations at zero sideslip

Experimental static aerodynamic forces and moments at high subsonic speeds on a missile model during simulated launching from unswept-, sweptback and modified-delta-wing-fuselage combinations at zero sideslip

Date: March 19, 1957
Creator: Alford, William J & King, Thomas J , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental static aerodynamic forces and moments at high subsonic speeds on a missile model during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage-pylon combination

Experimental static aerodynamic forces and moments at high subsonic speeds on a missile model during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage-pylon combination

Date: January 10, 1957
Creator: Alford, William J & King, Thomas, Jr
Description: An investigation was made at high subsonic speeds in the Langley high-speed 7- by 10-foot tunnel to determine the static aerodynamic forces and moments on a missile model during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage-pylon combination. The results indicated significant variations in all the aerodynamic components with changes in chordwise location of the missile. Increasing the angle of attack caused increases in the induced effects on the missile model because of the wing-fuselage-pylon combination. Increasing the Mach number had little effect on the variations of the missile aerodynamic characteristics with angle of attack except that nonlinearities were incurred at smaller angles of attack for the higher Mach numbers. The effects of finite wing thickness on the missile characteristics, at zero angle of attack, increase with increasing Mach number. The effects of the pylon on the missile characteristics were to causeincreases in the rolling-moment variation with angle of attack and a negative displacement of the pitching-moment curves at zero angle of attack. The effects of skewing the missile in the lateral direction relative to and sideslipping the missile with the wing-fuselage-pylon combination were to cause additional increments in side force at zero angle of attack. ...
Contributing Partner: UNT Libraries Government Documents Department
Theoretical and experimental investigation of the subsonic-flow fields beneath swept and unswept wings with tables or vortex-induced velocities

Theoretical and experimental investigation of the subsonic-flow fields beneath swept and unswept wings with tables or vortex-induced velocities

Date: January 1, 1957
Creator: Alford, William J , Jr
Description: The flow-field characteristics beneath swept and unswept wings as determined by potential-flow theory are compared with the experimentally determined flow fields beneath swept and unswept wing-fuselage combinations. The potential-flow theory utilized considered both spanwise and chordwise distributions of vorticity as well as the wing-thickness effects. The perturbation velocities induced by a unit horseshoe vortex are included in tabular form. The theoretical predictions of the flow-field characteristics were qualitatively correct in all cases considered, although there were indications that the magnitudes of the downwash angles tended to be overpredicted as the tip of the swept wing was approached and that the sidewash angles ahead of the unswept wing were underpredicted. The calculated effects of compressibility indicated that significant increases in the chordwise variation of flow angles and dynamic-pressure ratios should be expected in going from low to high subsonic speeds.
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of effects of moderate sideslip on the flow fields near a 45 degree swept-wing-fuselage combination at low speed

Experimental investigation of effects of moderate sideslip on the flow fields near a 45 degree swept-wing-fuselage combination at low speed

Date: July 12, 1957
Creator: Alford, William J , Jr & King, Thomas J , Jr
Description: The flow fields near a 45 degree swept-wing-fuselage combination at moderate angles of sideslip (plus-or-minus 8 degrees), as determined experimentally at low speed, are presented as variations with chordwise distance for various spanwise and vertical locations and angles of attack. The results indicated that for positions close to the fuselage (on and near the plane of symmetry) changes in the angle of sideslip caused large changes in the flow-field characteristics and particularly in the local angles of sideslip, which in some cases were nearly double the static angle of sideslip. In general, the effects of changing the angle of sideslip on the flow-field characteristics for all of the outboard underwing locations were qualitatively similar, although conditions at the more inboard and outboard locations were somewhat more severe for lifting conditions than at the one-half semispan location. The chordwise gradients in the flow parameters for the underwing locations were more severe than for the fuselage locations although the effect of changing the angle of sideslip was less severe, in that the incremental changes in the local angles of sideslip were approximately equal to the static angle of sideslip. Flow conditions near the wing tip were found to be critically dependent on ...
Contributing Partner: UNT Libraries Government Documents Department
Altitude chamber evaluation of an aircraft liquid hydrogen fuel system used with a turbojet engine

Altitude chamber evaluation of an aircraft liquid hydrogen fuel system used with a turbojet engine

Date: August 19, 1957
Creator: Algranti, J. S.; Braithwaite, W. M. & Fenn, D. B.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of vortex paths by series expansion technique with application to cruciform wings

Determination of vortex paths by series expansion technique with application to cruciform wings

Date: January 1, 1957
Creator: Alksne, Alberta Y
Description: A series method of determining two-dimensional vortex paths is considered and applied to the computation of vortex positions behind a slender equal-span cruciform wing at any angle of bank as a function of the distance behind the trailing edge. Calculated paths are shown for four bank angles. For a bank angle of 45 degrees comparison is made with the results of a closed expression given in NACA-TN-2605. For other bank angles water-tank experiments provide qualitative comparison. Satisfactory agreement is found for a sufficient distance downstream to include most practical missile-tail positions. The interference forces on an equal-span cruciform wing are calculated for five angles of bank (including the trivial case of zero bank) from the vortex positions found by use of the series.
Contributing Partner: UNT Libraries Government Documents Department
Heat of Combustion of the Product Formed by the Reaction of Acetylene and Diborane (LFPL-CZ-3)

Heat of Combustion of the Product Formed by the Reaction of Acetylene and Diborane (LFPL-CZ-3)

Date: October 24, 1957
Creator: Allen, Harrison, Jr. & Tannenbaum, Stanley
Description: The heat of combustion of the product formed by the reaction acetylene and diborane was found to be 20,100 +/- 100 Btu per pound for the reaction of liquid fuel to gaseous carbon dioxide, gaseous water, and solid boric oxide. The measurements were made in a Parr oxygen-bomb calorimeter, and chemical analyses both of the sample and of the combustion products indicated combustion in the bomb calorimeter to have been 97 percent complete. The estimated net heat of combustion for complete combustion would therefore be 20,700 +/- 100 Btu per pound.
Contributing Partner: UNT Libraries Government Documents Department
Motion of a ballistic missile angularly misaligned with the flight path upon entering the atmosphere and its effect upon aerodynamic heating, aerodynamic loads, and miss distance

Motion of a ballistic missile angularly misaligned with the flight path upon entering the atmosphere and its effect upon aerodynamic heating, aerodynamic loads, and miss distance

Date: October 1, 1957
Creator: Allen, Julian H
Description: An analysis is given of the oscillating motion of a ballistic missile which upon entering the atmosphere is angularly misaligned with respect to the flight path. The history of the motion for some example missiles is discussed from the point of view of the effect of the motion on the aerodynamic heating and loading. The miss distance at the target due to misalignment and to small accidental trim angles is treated. The stability problem is also discussed for the case where the missile is tumbling prior to atmospheric entry.
Contributing Partner: UNT Libraries Government Documents Department
A study of the motion and aerodynamic heating of missiles entering the earth's atmosphere at high supersonic speeds

A study of the motion and aerodynamic heating of missiles entering the earth's atmosphere at high supersonic speeds

Date: October 1, 1957
Creator: Allen, Julian H & Eggers, A J , Jr
Description: A simplified analysis of the velocity and deceleration history of missiles entering the earth's atmosphere at high supersonic speeds is presented. The results of this motion analysis are employed to indicate means available to the designer for minimizing aerodynamic heating. The heating problem considered involves not only the total heat transferred to a missile by convection, but also the maximum average and local time rates of convective heat transfer.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic performance of several techniques for spike-position control of  a blunt-lip nose inlet having internal contraction; Mach numbers of 0.63 and 1.5 to 2.0

Aerodynamic performance of several techniques for spike-position control of a blunt-lip nose inlet having internal contraction; Mach numbers of 0.63 and 1.5 to 2.0

Date: September 17, 1957
Creator: Anderson, Arthur A & Weinstein, Maynard I
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Use of Constant Diffuser Mach Number as a Control Parameter for Variable-geometry Inlets at Mach Numbers of 1.8 to 2.0

Use of Constant Diffuser Mach Number as a Control Parameter for Variable-geometry Inlets at Mach Numbers of 1.8 to 2.0

Date: November 4, 1957
Creator: Anderson, B. H. & Hearth, D. P.
Description: Control of variable-geometry inlets at constant mach numbers with blunt lip diffuser.
Contributing Partner: UNT Libraries Government Documents Department
Performance Comparison at Mach Numbers 1.8 and 2.0 of Full Scale and Quarter Scale Translating-Spike Inlets

Performance Comparison at Mach Numbers 1.8 and 2.0 of Full Scale and Quarter Scale Translating-Spike Inlets

Date: October 21, 1957
Creator: Anderson, B. H.; Dryer, M. & Hearth, D. P.
Description: The performance of a full-scale translating-spike inlet was obtained at Mach numbers of 1.8 and 2.0 and at angles of attach from 0 deg to 6 deg. Comparisons were made between the full-scale production inlet configuration and a geometrically similar quarter-scale model. The inlet pressure-recovery, cowl pressure-distribution, and compressor-face distortion characteristics of the full-scale inlet agreed fairly well with the quarter-scale results. In addition, the results indicated that bleeding around the periphery ahead of the compressor-face station improved pressure recovery and compressor-face distortion, especially at angle of attack.
Contributing Partner: UNT Libraries Government Documents Department
Some research results on sandwich structures

Some research results on sandwich structures

Date: June 1, 1957
Creator: Anderson, Melvin S & Updegraff, Richard G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation of the low-speed characteristics of a 35 degree swept-wing airplane equipped with an area-suction ejector flap and various wing leading-edge devices

Flight investigation of the low-speed characteristics of a 35 degree swept-wing airplane equipped with an area-suction ejector flap and various wing leading-edge devices

Date: September 26, 1957
Creator: Anderson, Seth B & Faye, Alan E , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Performance of 110-millimeter-bore M-1 tool steel ball bearings at high speeds, loads, and temperatures

Performance of 110-millimeter-bore M-1 tool steel ball bearings at high speeds, loads, and temperatures

Date: January 1, 1957
Creator: Anderson, William J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation at transonic speeds of loading over a 30 degree sweptback wing of aspect ratio 3, taper ratio 0.2, and NACA 65A004 airfoil section mounted on a body

Investigation at transonic speeds of loading over a 30 degree sweptback wing of aspect ratio 3, taper ratio 0.2, and NACA 65A004 airfoil section mounted on a body

Date: September 26, 1957
Creator: Arabian, Donald D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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