You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Decade: 1950-1959
 Year: 1953
Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics : effect of compressor interstage air bleed

Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics : effect of compressor interstage air bleed

Date: July 3, 1953
Creator: Rebeske, John J , Jr & Dugan, James F , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics I : effect of air bleed at compressor outlet

Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics I : effect of air bleed at compressor outlet

Date: March 10, 1953
Creator: Rebeske, John J , Jr & Rohlik, Harold E
Description: An analytical investigation was made to determine from component performance characteristics the effect of air bleed at the compressor outlet on the acceleration characteristics of a typical high-pressure-ratio single-spool turbojet engine. Consideration of several operating lines on the compressor performance map with two turbine-inlet temperatures showed that for a minimum acceleration time the turbine-inlet temperature should be the maximum allowable, and the operating line on the compressor map should be as close to the surge region as possible throughout the speed range. Operation along such a line would require a continuously varying bleed area. A relatively simple two-step area bleed gives only a small increase in acceleration time over a corresponding variable-area bleed. For the modes of operation considered, over 84 percent of the total acceleration time was required to accelerate through the low-speed range ; therefore, better low-speed compressor performance (higher pressure ratios and efficiencies) would give a significant reduction in acceleration time.
Contributing Partner: UNT Libraries Government Documents Department
Accelerations and passenger harness loads measured in full-scale light-airplane crashes

Accelerations and passenger harness loads measured in full-scale light-airplane crashes

Date: August 1953
Creator: Eiband, A Martin; Simpkinson, Scott H & Black, Dugald O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Adhesive and protective characteristics of ceramic coating A-417 and its effect on engine life of forged Refractaloy-26 (AMS 5760) and cast stellite 21 (AMS 5385) turbine blades

Adhesive and protective characteristics of ceramic coating A-417 and its effect on engine life of forged Refractaloy-26 (AMS 5760) and cast stellite 21 (AMS 5385) turbine blades

Date: February 12, 1953
Creator: Garrett, Floyd B & Gyorgak, Charles A
Description: The adhesive and protective characteristics of National Bureau of Standards Coating A-417 were investigated, as well as the effect of the coating on the life of forged Refractaloy 26 and cast Stellite 21 turbine blades. Coated and uncoated blades were run in a full-scale J33-9 engine and were subjected to simulated service operations consisting of consecutive 20-minute cycles (15 min at rated speed and approximately 5 min at idle). The ceramic coating adhered well to Refractaloy 26 and Stellite 21 turbine blades operated at 1500 degrees F. The coating also prevented corrosion of the Refractaloy 26, a corrosion-sensitive nickel-base alloy, and of the Stellite 21, a relatively corrosion-resistant cobalt-base alloy. Although the coating prevented corrosion of both alloys, it had no apparent effect on blade life.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at high and low subsonic Mach numbers of four NACA 6-series airfoil sections at angles of attack from -2 to 31 degrees

Aerodynamic characteristics at high and low subsonic Mach numbers of four NACA 6-series airfoil sections at angles of attack from -2 to 31 degrees

Date: June 5, 1953
Creator: Wilson, Homer B , Jr & Horton, Elmer A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics at Mach number 4.04 of a rectangular wing of aspect ratio 1.33 having a 6-percent-thick circular-arc profile and a 30-percent-chord full-span trailing-edge flap

Aerodynamic characteristics at Mach number 4.04 of a rectangular wing of aspect ratio 1.33 having a 6-percent-thick circular-arc profile and a 30-percent-chord full-span trailing-edge flap

Date: May 29, 1953
Creator: Dunning, Robert W & Ulmann, Edward F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics at transonic speeds of an all-movable, tapered, 45 degree sweptback, aspect-ratio-4 tail deflected about a skewed hinge axis and equipped with an inset unbalancing tab

The aerodynamic characteristics at transonic speeds of an all-movable, tapered, 45 degree sweptback, aspect-ratio-4 tail deflected about a skewed hinge axis and equipped with an inset unbalancing tab

Date: September 29, 1953
Creator: Watson, James M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics in Pitch and Sideslip at High Subsonic Speeds of a 1/14-Scale Model of the Grumman XF104 Airplane with Wing Sweepback of 42.5 Degrees

Aerodynamic Characteristics in Pitch and Sideslip at High Subsonic Speeds of a 1/14-Scale Model of the Grumman XF104 Airplane with Wing Sweepback of 42.5 Degrees

Date: January 1, 1953
Creator: Kuhn, Richard E. & Draper, John W.
Description: An investigation has been made at high subsonic speeds of the aerodynamic'characteristics in pitch and sideslip of a l/l4-scale model of the Grumman XF10F airplane with a wing sweepback angle of 42.5. The longitudinal stability characteristics (with the horizontal tail fixed) indicate a pitch-up near the stall; however, this was somewhat alleviated by the addition of fins to the side of the fuselage below the horizontal tail. The original model configuration became directionally unstable for small sideslip angles at Mach numbers above 0.8; however, the instability was eliminated by several different modifications.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics in pitch of a series of cruciform-wing missiles with canard controls at a Mach number of 2.01

Aerodynamic characteristics in pitch of a series of cruciform-wing missiles with canard controls at a Mach number of 2.01

Date: October 30, 1953
Creator: Spearman, M Leroy
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a 68.4 degree delta wing at Mach numbers of 1.6 and 1.9 over a wide Reynolds number range

Aerodynamic characteristics of a 68.4 degree delta wing at Mach numbers of 1.6 and 1.9 over a wide Reynolds number range

Date: November 2, 1953
Creator: Hatch, John E , Jr & Gallagher, James J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a refined deep-step planing-tail flying-boat hull with various forebody and afterbody shapes

Aerodynamic characteristics of a refined deep-step planing-tail flying-boat hull with various forebody and afterbody shapes

Date: January 1, 1953
Creator: Riebe, John M & Naeseth, Rodger L
Description: An investigation was made in the Langley 300 mph 7-by 10-foot tunnel to determine the aerodynamic characteristics of a refined deep-step planing-tail hull with various forebody and afterbody shapes. For comparison, tests were made on a streamline body simulating the fuselage of a modern transport airplane. The results of the tests, which include the interference effects of a 21-percent-thick support wing, indicated that for corresponding configurations the hull models incorporating a forebody with a length-beam ratio of 7 had lower minimum drag coefficients than the hull models incorporating a forebody with a length-beam ratio of 5. Longitudinal and lateral stability was generally about the same for all hull models tested and about the same as that of a conventional hull.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller

Aerodynamic characteristics of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller

Date: January 1, 1953
Creator: Solomon, William
Description: Characteristics are given for the two-blade NACA 10-(3)(062)-045 propeller and for the two-blade NACA 10-(3)(08)-045 propeller over a range of advance ratio from 0.5 to 3.8, through a blade-angle range from 20 degrees to 55 degrees measured at the 0.75 radius. Maximum efficiencies of the order of 91.5 to 92 percent were obtained for the propellers. The propeller with the thinner airfoil sections over the outboard portion of the blades, the NACA 10-(3)(062)-045 propeller, had lower losses at high tip speeds, the difference amounting to about 5 percent at a helical tip Mach number of 1.10.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic characteristics of an aspect-ratio-20 wing having thick airfoil sections and employing boundary-layer control by suction

The aerodynamic characteristics of an aspect-ratio-20 wing having thick airfoil sections and employing boundary-layer control by suction

Date: August 1, 1953
Creator: Cocke, Bennie W , Jr & Fink, Marvin P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Characteristics of Low-aspect-ratio Wings at High Supersonic Mach Numbers

Aerodynamic Characteristics of Low-aspect-ratio Wings at High Supersonic Mach Numbers

Date: November 2, 1953
Creator: Bertram, M. H. & Ulmann, E. F.
Description: Aerodynamic characteristics of low-aspect-ratio wings at supersonic speeds.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of low-aspect-ratio wings at high supersonic Mach numbers

Aerodynamic characteristics of low-aspect-ratio wings at high supersonic Mach numbers

Date: November 2, 1953
Creator: Ulmann, Edward F & Bertram, Mitchel H
Description: This paper presents some recently obtained data on the aerodynamic characteristics of low-aspect-ratio wings at supersonic Mach numbers of 4.04 and 6.9 and discusses some new methods of predicting the lift and drag of such wings. Data on lifting wings in the Mach number range above 2.5 are not plentiful and most of the available data may be found in NACA RM L51D17, NACA RM L51D30, NACA RM L52D15a, NACA RM L52K19, NACA RM L53D03, and NACA RM L53D30a.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic design and calibration of an asymmetric variable Mach number nozzle with a sliding block for the Mach number range 1.27 to 2.75

The aerodynamic design and calibration of an asymmetric variable Mach number nozzle with a sliding block for the Mach number range 1.27 to 2.75

Date: April 1, 1953
Creator: Burbank, Paige B & Byrne, Robert W
Description: A method of designing as asymmetric, fixed geometry, variable Mach number nozzle has been developed by using the method of characteristics. A small nozzle conforming to the analytically determined ordinates was constructed and calibrated over a range of Mach numbers extending from 1.27 to 2.75. The results show the variation in Mach number to be plus or minus 0.01 or less and in the flow direction to be plus or minus 0.2 degrees within the test section. The range of Mach numbers from 1.27 to 2.75 was obtained by translating the lower block in a straight line parallel to the test-section center line for a distance of 2.17 test-section heights.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic forces and loadings on symmetrical circular-arc airfoils with plain leading-edge and plain trailing-edge flaps

Aerodynamic forces and loadings on symmetrical circular-arc airfoils with plain leading-edge and plain trailing-edge flaps

Date: January 1, 1953
Creator: Cahill, Jones F; Underwood, William J; Nuber, Robert J & Cheesman, Gail A
Description: An investigation has been made in the Langley two-dimensional low-turbulence tunnel and in the Langley two-dimensional low-pressure tunnel of 6- and 10-percent-thick symmetrical circular-arc airfoil sections at low Mach numbers and several Reynolds numbers. The airfoils were equipped with 0.15-chord plain leading-edge flaps and 0.20-chord plan trailing-edge flaps. The section lift and pitching-moment characteristics were determined for both airfoils with the flaps deflected individually and in combination. The section drag characteristics were obtained for the 6-percent-thick airfoil with the flaps partly deflected as low-drag-control flaps and for airfoils with the flaps neutral. Surface pressures were measured on the 6-percent-thick airfoil section with the flaps deflected either individually or in appropriate combination to furnish flap load and hinge-moment data applicable to the structural design of the airfoil. A generalized method is developed that permits the determination of the chordwise pressure distribution over sharp-edge airfoils with plain leading-edge flaps and plain trailing-edge flaps of arbitrary size and deflection.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) III : boundary layer and force measurements on a slender cone-cylinder body of revolution

Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) III : boundary layer and force measurements on a slender cone-cylinder body of revolution

Date: April 6, 1953
Creator: Jack, John R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aeronautical Lab. Examination of Recent Lateral-stability-derivative Data

Aeronautical Lab. Examination of Recent Lateral-stability-derivative Data

Date: October 22, 1953
Creator: Kuhn, R. F. & Malvestuto, F. S., Jr.
Description: Stability derivatives affecting lateral behavior of aircraft and missiles.
Contributing Partner: UNT Libraries Government Documents Department
Aileron and Elevator Hinge Moments of the Bell X-1 Airplane Measured in Transonic Flight

Aileron and Elevator Hinge Moments of the Bell X-1 Airplane Measured in Transonic Flight

Date: June 22, 1953
Creator: Drake, Hubert M & Mckay, John B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Air admixture to exhaust jets

Air admixture to exhaust jets

Date: July 1, 1953
Creator: Sanger, Eugen
Description: The problem of thrust increase by air admixture to exhaust jets of rockets, turbojet, ram- and pulse-jet engines is investigated theoretically. The optimum ratio of mixing chamber pressure to ambient pressure and speed range for thrust increase due to air admixture is determined for each type of jet engine.
Contributing Partner: UNT Libraries Government Documents Department
Air-flow and thrust characteristics of several cylindrical cooling-air ejectors with a primary to secondary temperature ratio of 1.0

Air-flow and thrust characteristics of several cylindrical cooling-air ejectors with a primary to secondary temperature ratio of 1.0

Date: March 6, 1953
Creator: Greathouse, W K & Hollister, D P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Air-flow characteristics of brazed and rolled wire filter cloth for transpiration-cooled afterburners

Air-flow characteristics of brazed and rolled wire filter cloth for transpiration-cooled afterburners

Date: October 26, 1953
Creator: Koffel, William K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Air-water analogy and the study of hydraulic models

Air-water analogy and the study of hydraulic models

Date: July 1, 1953
Creator: Supino, Giulio
Description: The author first sets forth some observations about the theory of models. Then he established certain general criteria for the construction of dynamically similar models in water and in air, through reference to the perfect fluid equations and to the ones pertaining to viscous flow. It is, in addition, pointed out that there are more cases in which the analogy is possible than is commonly supposed.
Contributing Partner: UNT Libraries Government Documents Department
FIRST PREV 1 2 3 4 5 NEXT LAST