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Stability of ballistic reentry bodies

Description: Report discussing various features of the stability of ballistic reentry shapes, including considerations for ballistic-missile and manned-satellite reentry capsules. Attainment of satisfactory stability of reentry bodies with subsonic terminal velocities was not found to be too difficult, but undesirable features that may cause marginal stability characteristics may be introduced in an effort to minimize weight. Reentry bodies with supersonic terminal velocities have fewer stability issues.
Date: August 11, 1958
Creator: Bird, John D. & Reese, David E., Jr.
Partner: UNT Libraries Government Documents Department

Wind tunnel investigation at high subsonic speeds of drag at 0 degrees angle of attack of swept-wing fuselage models with pylon mounted and semisubmerged missiles

Description: Report discussing testing on two wing-fuselage models with 45 degree sweptback wings and various missile arrangements, one with pylons underneath the wing and one with the missiles semisubmerged in the sides of the fuselage. A comparison of the drag of both types of models was made.
Date: October 8, 1956
Creator: King, Thomas J., Jr.
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 degree sweptback wing-fuselage-pylon combination at zero sideslip

Description: Report presenting an investigation at high subsonic speeds to determine the static aerodynamic forces and moments on a canard missile model during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage-pylon combination. Significant variations in all the aerodynamic components were noted with changes in chordwise location of the missile. Results regarding force and moment characteristics and effects of angle of attack and Mach number are provided.
Date: January 14, 1957
Creator: Alford, William J., Jr. & King, Thomas J., Jr.
Partner: UNT Libraries Government Documents Department

Investigation of the static stability characteristics of five hypersonic missile configurations at Mach numbers from 2.29 to 4.65

Description: Report presenting an investigation to determine the static stability characteristics of five hypersonic missile configurations. Testing was performed at a range of Mach and Reynolds numbers. Results regarding the effect of base block, longitudinal stability, directional stability, and Reynolds number effect are provided.
Date: June 30, 1958
Creator: Turner, Kenneth L. & Appich, W. H., Jr.
Partner: UNT Libraries Government Documents Department

Transonic flutter characteristics of a cambered A-plan-form wing with and without simulated nacelles

Description: Report presenting an experimental investigation to determine the effects of simulated engine nacelles on the flutter characteristics of a cambered A-plan-form wing with 45 degree sweepback of the leading edge, an aspect ratio of 3.6, and a taper ratio of 0.14. Results regarding a wing-mount fixed and a model with wing mount free are provided.
Date: July 10, 1957
Creator: Kelly, H. Neale
Partner: UNT Libraries Government Documents Department

Hydrodynamic Characteristics of a Low-Drag, Planing-Tail Flying-Boat Hull

Description: Report discussing the hydrodynamic characteristics of a flying boat with a low-drag, planing-tail hull compared with a conventional-type hull. The planing-tail model had more take-off stability than the conventional model and had lower hydrodynamic resistance. Information about the landing stability, variation of trim with speed, and spray characteristics is also provided.
Date: October 21, 1948
Creator: Suydam, Henry B.
Partner: UNT Libraries Government Documents Department

Additional abstracts pertaining to seaplanes

Description: From Summary: "About 500 additional references pertaining to hydrodynamic design of seaplanes have been compiled, and the information is presented in the form of abstracts classified under six main headings:GENERAL INFORMATION, HYDROSTATICS, HYDRODYNAMICS, AERODYNAMICS, OPERATION, and RESEARCH. The compilation is an extension of NACA RM No. L6I13, entitled "Abstracts Pertaining to Seaplanes," by Jerold M. Bidwell and Douglas A. King. An author index and a subject index are included."
Date: March 9, 1948
Creator: Bidwell, J. M. & King, D. A.
Partner: UNT Libraries Government Documents Department

Turbine Engines for High-Speed Flight

Description: This analysis investigates the application of gas turbine engines at a cruise Mach number of 4.
Date: 1958
Creator: Henneberry, Hugh M. & Zimmerman, Arthur V.
Partner: UNT Libraries Government Documents Department

Comparison of free-flight measurements of the zero-lift drag rise of six airplane configurations and their equivalent bodies of revolution at transonic speeds

Description: From Summary: "Free-flight drag measurements are presented which show the practicability of duplicating the zero-lift drag rise of many airplane configurations by simple bodies of revolution. The results confirm the transonic area rule for straight wings, and for delta and modified-delta wings with and without nacelles. The results showed that the area rule did not apply to one swept-wing configuration and an explanation is advanced to explain why it does not apply."
Date: January 5, 1954
Creator: Hall, James Rudyard
Partner: UNT Libraries Government Documents Department

Comparison of wind-tunnel, rocket, and flight drag measurements for eight airplane configurations at Mach numbers between 0.7 and 1.6

Description: Report presenting comparisons of low-lift drag measurements on eight airplane configurations at a range of Mach numbers by various techniques. Data was obtained from wind tunnel testing, rocket propelled model tests, and airplane flight tests. The agreement of data is generally good and no consistent Reynolds number effects are observed.
Date: September 16, 1954
Creator: Purser, Paul E.
Partner: UNT Libraries Government Documents Department

Flight characteristics of a wingless rocket- powered model with four externally mounted air-to-air missiles at Mach numbers 0.7 to 1.6

Description: Report presenting a flight investigation of four air-to-air missiles mounted by pylons on a rocket-powered basic wingless buffet-research vehicle to determine the trim, buffet, and drag characteristics of the combination.
Date: January 25, 1955
Creator: Henning, Allen B. & Brown, Clarence A., Jr.
Partner: UNT Libraries Government Documents Department

Rocket-model investigation of the longitudinal stability, drag, and duct performance of a 60 degree delta-wing canard aircraft with twin side inlets at Mach numbers from 0.80 to 1.70

Description: Report discussing a flight test on a rocket-boosted canard aircraft with 60 degree delta lifting surfaces, twin normal-shock-type side inlets, and twin vertical tails. The drag, longitudinal stability, and duct performance data were obtained for a range of Mach and Reynolds numbers.
Date: March 29, 1954
Creator: Bond, Aleck C. & Swanson, Andrew G.
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

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.
Date: October 21, 1957
Creator: Anderson, B. H.; Dryer, M. & Hearth, D. P.
Partner: UNT Libraries Government Documents Department

An Investigation of the Effects of Nose and Lip Shapes for an Underslung Scoop Inlet at Mach Numbers from 0 to 1.9

Description: An experimental investigation was conducted to determine the performance characteristics an underslung nose-scoop air-induction system for a supersonic airplane. Five different nose shapes, three lip shapes, and two internal diffusers were investigated. Tests were made at Mach numbers from 0 to 1.9, angles of attack from 0 deg to approximately l5 deg, and mass-flow ratios from 0 to maximum obtainable. It was found that the underslung nose-scoop inlet was able to operate at Mach numbers from 0.6 to 1.9 over a large positive angle-of-attack range without adverse effects on the pressure recovery. Although there was no one inlet configuration that was markedly superior over the entire range of operating variables, the arrangement having a nose designed to give increased supersonic compression at low angles of attack, and a sharp lip (configuration designated N3L3) showed the most favorable performance characteristics over the supersonic Mach number range. Inlets with sizable lip radii gave satisfactory performance up to a Mach number of 1.5; however, as a result of an increase in drag, the performance of such inlets was markedly inferior to the sharp-lip configuration above Mach numbers of 1.5. Throughout the range of test Mach numbers all inlet configurations evidenced stable air-flow characteristics over the mass-flow range for normal engine operation. Analysis of the inlet performance on the basis of a propulsive thrust parameter showed that a fixed inlet area could be used for Mach numbers up to 1.5 with only a small sacrifice in performance.
Date: November 18, 1955
Creator: Pfyl, Frank A.
Partner: UNT Libraries Government Documents Department

Some effects of roll rate on the longitudinal stability characteristics of a cruciform missile configuration as determined from flight test for a Mach number range of 1.1 to 1.8

Description: Report discussing testing of a cruciform missile with a low-aspect-ratio wing and flap-type controls to determine the stability and control characteristics while rolling. Longitudinal stability and control effectiveness for this particular configuration were examined. The data obtained was compared to results from a similar model that was rolling significantly less.
Date: June 19, 1956
Creator: Lundstrom, Reginald R. & Baber, Hal T., Jr.
Partner: UNT Libraries Government Documents Department

Flight test of a solid-fuel ramjet with the internal surface of the combustor air cooled

Description: Report presenting a flight investigation of a rocket-launched solid-fuel ram-jet engine designed to bypass cooling air around the fuel charge. The internally cooled combustor averted combustor burn-out during the flight test. Results regarding the net thrust coefficient, gross thrust coefficient, time history of the air specific impulse, and total fuel load are provided.
Date: July 3, 1956
Creator: Bartlett, Walter A., Jr.
Partner: UNT Libraries Government Documents Department

Longitudinal stability and control characteristics as determined by the rocket-model technique for an inline, cruciform, canard missile configuration with a low-aspect-ratio wing having trailing-edge flap controls for a Mach number range of 0.7 to 1.8

Description: Report presenting testing of two full-scale models of an inline, cruciform, canard missile configuration with a low-aspect-ratio wing equipped with flap-type controls to determine the missile's longitudinal aerodynamic characteristics. Stability derivatives and control and drag characteristics are provided.
Date: September 28, 1955
Creator: Baber, Hal T., Jr. & Moul, Martin T.
Partner: UNT Libraries Government Documents Department

Flight test of an end-burning solid-fuel ramjet

Description: Report presenting a flight investigation of a rocket-launched ram-jet engine incorporating an end-burning solid fuel. Results regarding acceleration, altitude, booster separation, survival time of booster adapter, and air specific impulse are provided.
Date: March 25, 1954
Creator: Bartlett, Walter A., Jr.
Partner: UNT Libraries Government Documents Department