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  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Year: 1957
 Collection: Technical Report Archive and Image Library
Aerodynamic characteristics of a circular cylinder at Mach number 6.86 and angles of attack up to 90 degrees

Aerodynamic characteristics of a circular cylinder at Mach number 6.86 and angles of attack up to 90 degrees

Date: January 1, 1957
Creator: Penland, Jim A
Description: Pressure-distribution and force tests of a circular cylinder have been made in the Langley 11-inch hypersonic tunnel at a Mach number of 6.88, a Reynolds number of 129,000, and angles of attack up to 90 degrees. The results are compared with the hypersonic approximation of Grimminger, Williams, and Young and a simple modification of the Newtonian flow theory. An evaluation of the crossflow theory is made through comparison of present results with available crossflow Mach number drag coefficients.
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 Forces on a Vibrating Unstaggered Cascade

Aerodynamic Forces on a Vibrating Unstaggered Cascade

Date: August 1, 1957
Creator: Soehngen, H.
Description: The unsteady aerodynamic forces, [based on two-dimensional incompressible flow considerations], are determined for an unstaggered cascade, the blades of which are vibrating in phase in an approach flow parallel to the blades.
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
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
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic interference of slender wing-tail combinations

Aerodynamic interference of slender wing-tail combinations

Date: January 1, 1957
Creator: Sacks, Alvin H
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
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.
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