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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Year: 1957
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
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
Additional experiments with flat-top wing- body combinations at high supersonic speeds

Additional experiments with flat-top wing- body combinations at high supersonic speeds

Date: February 19, 1957
Creator: Gloria, H. R.; Syvertson, C. A. & Wong, T. J.
Description: Flat top wing body configuration effects on aerodynamic characteristics of supersonic aircraft.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic and hydrodynamic characteristics of a proposed supersonic multijet water-based hydro-ski aircraft with a variable-incidence wing

Aerodynamic and hydrodynamic characteristics of a proposed supersonic multijet water-based hydro-ski aircraft with a variable-incidence wing

Date: October 23, 1957
Creator: Petynia, William W; Hasson, Dennis F & Spooner, Stanley H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at Mach number of 4.06 of a typical supersonic airplane model using body and vertical-tail wedges to improve directional stability

Aerodynamic characteristics at Mach number of 4.06 of a typical supersonic airplane model using body and vertical-tail wedges to improve directional stability

Date: December 3, 1957
Creator: Dunning, Robert W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair TF-102A Airplane at Transonic Speeds, Coord. No. AF-120

Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair TF-102A Airplane at Transonic Speeds, Coord. No. AF-120

Date: 1957~
Creator: Osborne, Robert S.
Description: The basic aerodynamic characteristics of a 0.04956-scale model of the Convair TF-102A airplane with controls undeflected have been determined at Mach numbers from 0.60 to 1.135 for angles of attack up to approximately 22 deg in the Langley 8-foot transonic tunnel. In addition, comparisons have been made with data obtained from a previous investigation of a 0.04956-scale model of the Convair F-102A airplane. The results indicated the TF-102A airplane was longitudinally stable for all conditions tested. An increase in lift-curve slope from 0.045 to 0.059 and an 11-percent rearward shift in aerodynamic-center location occurred with increases in Mach number from 0.60 to approximately 1.05. The zero-lift drag coefficient for the TF-102A airplane increased 145 percent between the Mach numbers of 0.85 and 1.075; the maximum lift-drag ratio decreased from 9.5 at a Mach number of 0.60 to 5.0 at Mach numbers above 1.025. There was little difference in the lift and pitching-moment characteristics and drag due to life between the TF-102A and F-102A configurations. However, as compared with the F-102A airplane, the zero-lift drag-rise Mach number for the TF-102A was reduced by at least 0.06, the zero-lift peak wave drag was increased 50 percent, and the maximum lift-drag ratio was ...
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics of a body in the two-dimensional flow field of a circular-arc wing at a Mach number of 2.01

The aerodynamic characteristics of a body in the two-dimensional flow field of a circular-arc wing at a Mach number of 2.01

Date: July 2, 1957
Creator: Gapcynski, John P & Carlson, Harry W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a model of an escape capsule for a supersonic bomber-type airplane at a Mach number of 2.49

Aerodynamic characteristics of a model of an escape capsule for a supersonic bomber-type airplane at a Mach number of 2.49

Date: December 3, 1957
Creator: Presnell, John G , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of missile configurations with wings of low aspect ratio for various combinations of forebodies, afterbodies, and nose shapes for combined angles of attack and sideslip at a Mach number of 2.01

Aerodynamic characteristics of missile configurations with wings of low aspect ratio for various combinations of forebodies, afterbodies, and nose shapes for combined angles of attack and sideslip at a Mach number of 2.01

Date: June 25, 1957
Creator: Robinson, Ross B
Description: An investigation has been made in the Langley 4-by-4-foot supersonic pressure tunnel to determine the aerodynamic characteristics of a series of missile configurations having low-aspect-ratio wings at a Mach number of 2.01. The effects of wing plan form and size, length-diameter ratio, forebody and afterbody length, boattailed and flared afterbodies, and component force and moment data are presented for combined angles of attack and sideslip to about 28 degrees. No analysis of the data was made in this report.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Forces and Moments on a Large Ogive-Cylinder Store at Various Locations Below the Fuselage Center Line of a Swept-Wing Bomber Configuration at a Mach Number of 1.61

Aerodynamic Forces and Moments on a Large Ogive-Cylinder Store at Various Locations Below the Fuselage Center Line of a Swept-Wing Bomber Configuration at a Mach Number of 1.61

Date: January 14, 1957
Creator: Morris, O. A.
Description: A supersonic wind-tunnel investigation on store interference has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.61. Forces and moments were measured on a large ogive-cylinder store in the presence of a 45 deg swept-wing-fuselage bomber configuration for a number of store locations below the fuselage center line. Results of the investigation show that large variations of store lift, drag, and pitch occur with changes in store or airplane angle of attack, store vertical location, and store horizontal location. The variation of the store forces and moments with respect to the chordwise location of the wing plan form indicates that the wing is a large factor in producing the interference loads on the store. Comparison of data for underfuselage and underwing store locations at an angle of attack of 0 deg showed maximum store drag interferences of similar magnitudes, but showed considerably smaller maximum interference on store lift an pitching moments for underfuselage store locations.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Heating and Boundary-layer Transition on a 1/10-power nose shape in free flight at Mach numbers up to 6.7 and Free-stream Reynolds numbers up tp 16 x 10(exp 6)

Aerodynamic Heating and Boundary-layer Transition on a 1/10-power nose shape in free flight at Mach numbers up to 6.7 and Free-stream Reynolds numbers up tp 16 x 10(exp 6)

Date: June 17, 1957
Creator: Garland, Benjamine J; Swanson, Andrew G & Speegle, Katherine C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic heating of a thin, unswept, untapered, multiweb, aluminum-alloy wing at Mach numbers up to 2.67 as determined from a free-flight investigation of a rocket-propelled model

Aerodynamic heating of a thin, unswept, untapered, multiweb, aluminum-alloy wing at Mach numbers up to 2.67 as determined from a free-flight investigation of a rocket-propelled model

Date: August 6, 1957
Creator: Strass, H Kurt & Stephens, Emily W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic load distribution over a 45 degree swept wing having a spoiler-slot-deflector aileron and other spoiler ailerons for Mach numbers from 0.60 to 1.03

Aerodynamic load distribution over a 45 degree swept wing having a spoiler-slot-deflector aileron and other spoiler ailerons for Mach numbers from 0.60 to 1.03

Date: December 5, 1957
Creator: West, F E , Jr; Whitcomb, Charles F & Schmeer, James W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Loads on Tails at High Angles of Attack and Sideslip

Aerodynamic Loads on Tails at High Angles of Attack and Sideslip

Date: July 23, 1957
Creator: Polhamus, E. C. & Spahr, J. R.
Description: Results are presented for the loads and moments acting on the individual tail surfaces of a body-tail combination over a wide range of angles of attack and sideslip. The effects of forebody length and panel-panel interference on the characteristics are included. It is shown that large nonlinear variations in these loads and moments, which occur at some combinations of angle of attack and sideslip, cannot be predicted by low-angle theory. A relatively simple, but general, theoretical method for calculating these load and moment characteristics is described, and the results from this method are found to be in good agreement with experiment provided the initial positions of the forebody vortices are known. It is shown that a simple application of slender-body theory can be used to predict the side loads due to sideslip that are contributed by a vertical tail on a wide variety of wing-body-tail combinations at low angles of attack. For several configurations, changes are indicated which reduced the vertical-tail loads per unit yawing moment of each complete configuration at large angles of attack. Some results are presented on the effect of high angle of attack on the induced-flow field and tail loads due to a wing at supersonic ...
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
Aerodynamics of Oscillating Control Surfaces at Transonic Speeds

Aerodynamics of Oscillating Control Surfaces at Transonic Speeds

Date: June 17, 1957
Creator: Clevenson, S. A. & Thompson, R. F.
Description: Aerodynamic forces and moments of oscillating control surfaces at transonic speeds.
Contributing Partner: UNT Libraries Government Documents Department
An air-borne target simulator for use with scope-presentation type fire-control systems

An air-borne target simulator for use with scope-presentation type fire-control systems

Date: May 10, 1957
Creator: Foster, John V; Fulcher, Elmer C & Heinle, Donovan R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Airplane measurements of atmospheric turbulence for altitudes between 20,000 and 55,000 feet over the western part of the United States

Airplane measurements of atmospheric turbulence for altitudes between 20,000 and 55,000 feet over the western part of the United States

Date: August 23, 1957
Creator: Coleman, Thomas L & Coe, Emilie C
Description: None
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
Altitude free-jet investigation of dynamics of a 28-inch-diameter ram-jet engine

Altitude free-jet investigation of dynamics of a 28-inch-diameter ram-jet engine

Date: January 15, 1957
Creator: Crowl, R. J.; Dunbar, W. R. & Wentworth, C. B.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude performance of a full-scale turbojet engine using pentaborane fuels

Altitude performance of a full-scale turbojet engine using pentaborane fuels

Date: February 28, 1957
Creator: Useller, James W; Kaufman, Warner B & Jones, William L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude performance of a turbojet engine using pentaborane fuel

Altitude performance of a turbojet engine using pentaborane fuel

Date: May 20, 1957
Creator: Sivo, Joseph N
Description: A full-scale turbojet engine having a two-stage turbine was operated with pentaborane fuel continuously for 11.5 minutes at a simulated altitude of 55,000 feet at a flight Mach number of 0.8. The engine incorporated an NACA combustor designed specifically for use with pentaborane fuel. The specific fuel consumption was initially reduced 32 percent below that obtained with gasoline fuel; however, the occurrence of a 25-percent reduction in net thrust after 8 minutes of operation resulted in a subsequent increase in specific fuel consumption to a value only 11.5 percent lower than that for gasoline.
Contributing Partner: UNT Libraries Government Documents Department
Altitude performance of a turbojet engine using pentaborane fuel

Altitude performance of a turbojet engine using pentaborane fuel

Date: May 20, 1957
Creator: Sivo, J. N.
Description: Altitude performance of turbojet engine using pentaborane fuel.
Contributing Partner: UNT Libraries Government Documents Department
Altitude performance of pentaborane - JP-4 fuel blends in a modified J47 combustor

Altitude performance of pentaborane - JP-4 fuel blends in a modified J47 combustor

Date: April 17, 1957
Creator: Branstetter, J Robert & Kaufman, Warner B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude Starting Tests of a 1000-Pound-Thrust Solid-Propellant Rocket

Altitude Starting Tests of a 1000-Pound-Thrust Solid-Propellant Rocket

Date: September 13, 1957
Creator: Sloop, John L.; Rollbuhler, R. James & Krawczonek, Eugene M.
Description: Four solid-propellant rocket engines of nominal 1000-pound-thrust were tested for starting characteristics at pressure altitudes ranging from 112,500 to 123,000 feet and at a temperature of -75 F. All engines ignited and operated successfully. Average chamber pressures ranged from 1060 to ll90 pounds per square inch absolute with action times from 1.51 to 1.64 seconds and ignition delays from 0.070 t o approximately 0.088 second. The chamber pressures and action times were near the specifications, but the ignition delay was almost twice the specified value of 0.040 second.
Contributing Partner: UNT Libraries Government Documents Department
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