National Advisory Committee for Aeronautics (NACA) - 194 Matching Results

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Some Notes on the Probable Damage to an Intercontinental-Ballistic-Missile Warhead Following Puncture of the Heat Shield

Description: Report discussing a study of the effects of puncturing the heat shield of an intercontinental-ballistic-missile warhead by small projectiles. Calculations were created for both rod and sphere projectiles and experimental testing was performed on a missile model with holes drilled in the heat shield. The possibility that a projectile could have enough energy to cause mechanical damage to the interior of the warhead is also presented.
Date: September 29, 1958
Creator: Strass, H. K. & Goodman, V. M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Heat-Transfer and Pressure Measurements From a Flight Test of the Second 1/18-Scale Model of the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.91 and Reynolds Number Per Foot of 23.4 by 10 to the 6th Power

Description: Report discussing heat-transfer and pressure measurements obtained from flight testing of a model of the Titan intercontinental ballistic missile up to a specified Mach and Reynolds number. The heat-transfer coefficients were compared to theoretical results and a discrepancy was found during the accelerating portions of flight. Drag coefficients were obtained for a range of Mach numbers.
Date: January 29, 1958
Creator: Graham, John B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Heat-Transfer and Pressure Measurements From a Flight Test of the Second 1/18-Scale Model on the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.91 and Reynolds Number Per Foot of 23.4 X 10(Exp 6) : Coord. No. AF-AM-70

Description: Report presenting heat-transfer and pressure measurements obtained from flight tests of a model of the Titan intercontinental ballistic missile. Turbulent flow was observed over the model throughout the flight with the exception of one station on the nose. Results regarding pressure measurements, heat transfer, and drag measurements are required.
Date: January 29, 1958
Creator: Graham, John B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Drag Minimization for Wings and Bodies in Supersonic Flow

Description: "The minimization of inviscid fluid drag is studied for aerodynamic shapes satisfying the conditions of linearized theory, and subject to imposed constraints on lift, pitching moment, base area, or volume. The problem is transformed to one of determining two-dimensional potential flows satisfying either Laplace's or Poisson's equations with boundary values fixed by the imposed conditions. A general method for determining integral relations between perturbation velocity components is developed. … more
Date: November 29, 1957
Creator: Heaslet, Max A. & Fuller, Franklyn B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculation of External-Store Loads and Correlation With Experiment

Description: Memorandum presenting a theory for evaluating the mutual interference between a wing and tip tank as extended to apply to store-pylon configurations. By using the theory and the flow-field formulas of a previous report, theoretical store-pylon side-force estimates have been made for a number of store-pylon configurations. Results regarding the theory for store-pylon side force, scope of test configurations, contribution of store and pylon to combined load, effect of store spanwise location on t… more
Date: July 29, 1957
Creator: Bobbitt, Percy J.; Carlson, Harry W. & Pearson, Albin O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Exploratory investigation of aerodynamic effects of external combustion of aluminum borohydride in airstream adjacent to flat plate in Mach 2.46 tunnel

Description: Report presenting pressure distributions associated with stable combustion of aluminum borohydride in the supersonic stream adjacent to a short, 13-inch chord, and an extended, 25-inch chord, flat-plate model. High-speed direct and schileren motion pictures of the flame and associated shock waves were taken. Results regarding the description of the combustion and associated stream disturbances, static-pressure change at model reference surface caused by combustion, lift forces resulting from co… more
Date: July 29, 1957
Creator: Dorsch, Robert G.; Serafini, John S. & Fletcher, Edward A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Exploratory Tests of the Behavior of Several Materials in a Supersonic Air Jet at 4,000 Degrees Fahrenheit

Description: "Several materials have been tested in the ceramic-heated jet (laboratory model) at a Mach number of 1.96 with a stagnation temperature of approximately 4,000 degrees Fahrenheit. Test models made of molybdenum were less affected by temperature than titanium, stainless steel, and an alloy of 90 percent tungsten, 6 percent nickel, and 4 percent copper. Titanium and steel burn with highly exothermic reactions when subjected to the 4,000 degrees Fahrenheit air jet" (p. 1).
Date: July 29, 1957
Creator: Hopko, Russell N. & Trout, Otto F., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of the Low-Speed Performance and Static Longitudinal Stability and Control Characteristics of a 60 Degree Delta-Wing-Body-Tail Combination With Blowing Over Trailing-Edge Flaps

Description: Report presenting an investigation in the full-scale tunnel to determine the effects of boundary-layer control by blowing over trailing-edge flaps on the low-speed performance and static longitudinal stability characteristics of a 60 degree delta wing-body-tail combination with variable flap positioning and leading-edge devices. Results regarding the flap lift characteristics at zero angle of attack, tail-off characteristics, tail-on characteristics, and low-speed performance characteristics ar… more
Date: July 29, 1957
Creator: Scallion, William I. & Cannon, Michael D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

High-Altitude Performance of J71-A-11 Turbojet Engine and Its Components Using JP-4 and Gaseous-Hydrogen Fuels

Description: Report presenting data to determine the component and overall engine performance up to an altitude limit for the J71-A-11 (600-B36) turbojet engine. Engine operation using JP-4 fuel at Mach number 0.8 was satisfactory up to an altitude of about 60,000 to 65,000 feet, and engine operation with marginal combustion stability was maintained to an altitude of about 80,000 feet. Results regarding the altitude operating limits, component performance, overall engine performance, contribution of individ… more
Date: May 29, 1957
Creator: Smith, Ivan D. & Saari, Martin J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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High-Altitude Performance of J71-A-11 Turbojet Engine and Its Components Using JP-4 and Gaseous-Hydrogen Fuels

Description: Memorandum presenting an investigation of the J71-A-11 (600-B36) turbojet engine conducted in an altitude wind tunnel, and more specifically the component and overall engine performance up to the altitude limit imposed by the use of MIL-F-5624A, grade JP-4, fuel. The data were then extended to higher altitudes by the use of gaseous-hydrogen fuel. Results regarding altitude operating limits, component performance, overall engine performance, contribution of individual component losses to overall… more
Date: May 29, 1957
Creator: Smith, Ivan D. & Saari, Martin J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Inlet Modification and Rocket-Rack Extension on the Longitudinal Trim and Low-Lift Drag of the Douglas F5D-1 Airplane as Obtained with a 0.125-Scale Rocket-Boosted Model Between Mach Numbers of 0.81 and 1.64: TED No. NACA AD 399

Description: From Summary: "A flight investigation was conducted to determine the effects of inlet modification and rocket-rack extension on the longitudinal trim and low-lift drag of the Douglas F5D-1 airplane. The investigation was conducted with a 0.125-scale rocket-boosted model between Mach Numbers of 0.81 and 1.64. This paper presents the changes in trim angle of attack, trim lift coefficient, and low-lift drag caused by the modified inlets alone over a small part of the test Mach number range and by … more
Date: April 29, 1957
Creator: Hastings, Earl C., Jr. & Dickens, Waldo L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-Spinning-Tunnel Investigation of a 1/25-Scale Model of the McDonnell F3H-2N Airplane

Description: Memorandum presenting an investigation in the 20-foot free-spinning tunnel on a 1/25-scale model of the McDonnell F3H-2N airplane. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model were determined for the clean condition. Results regarding erect spins, engine gyroscopic moments, inverted spins, spin-recovery parachute, and landing condition tests are provided.
Date: April 29, 1957
Creator: Lee, Henry A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation and Theoretical Calculations of the Fuselage Deformations of a Swept-Wing Bomber During Push-Pull Maneuvers

Description: Report presenting the results of fuselage-deflection measurements at three stations on the fuselage of a swept-wing bomber (Boeing B-47A) during 12 push-pull maneuvers. The results are provided in the form of coefficients expressing the fuselage deflection due to normal-acceleration loads, pitching angular-acceleration loads, pitching angular-velocity loads, and the combined effect of zero-lift loads, fuselage dead weight, and landing-gear reactions. Comparisons of the theoretical and experimen… more
Date: March 29, 1957
Creator: Mayo, Alton P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Leading-Edge Contours for Thin Swept Wings: An Analysis of Low-and High-Speed Data

Description: Memorandum presenting a review of important aspects of current data on thin swept wings with bulbous leading-edge contours. The outboard concentration of a bulbous contour will generally yield most or all of the characteristics low-speed benefit attainable from the use of such a contour. Results regarding data at low speeds, data at high speeds, implications of the data regarding outboard bulbous contours, and area-rule considerations and data are provided.
Date: March 29, 1957
Creator: Evans, William T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Preliminary Analysis of the Magnitude of Shock Losses in Transonic Compressors

Description: Report presenting a review of the possible shock system associated with the supersonic blade elements encountered in transonic-compressor rotors. The variation of shock shape and location with operating conditions is described. Results regarding flow, estimated shock losses at maximum element efficiency, and profile losses are provided.
Date: March 29, 1957
Creator: Schwenk, Francis C.; Lewis, George W. & Hartmann, Melvin J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-flight investigation at Mach numbers between 0.5 and 1.7 of the zero-lift rolling effectiveness and drag of various surface, spoiler, and jet controls on an 80 degree delta-wing missile

Description: Report presenting a free-flight investigation of the zero-lift rolling effectiveness and drag of 18 roll-control arrangements on a cruciform 80 degree delta-wing missile-like configuration over a range of Mach numbers. Testing was made of deflected surfaces, spoilers, and inlet-air-jet devices to give evidence to simple theory for deflected surfaces and to determine some effects of chordwise location for spoilers and blowing direction and spanwise location for jets near the wing trailing edge. … more
Date: November 29, 1956
Creator: Schult, Eugene D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation at Supersonic Speeds of the Effects of Bomb-Bay Configuration Upon the Aerodynamic Characteristics of Fuselages With Noncircular Cross Sections

Description: Memorandum presenting an investigation in the 9-inch supersonic tunnel to ascertain the lift, drag, and pitching moments of typical body-bomb-bay configurations with and without the bomb. The bodies had elliptical, triangular, and teardrop cross sections. Results regarding effects of angle-of-attack variation and effects of Mach number variation are provided.
Date: November 29, 1956
Creator: Rainey, Robert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of separated flows in supersonic and subsonic streams with emphasis on the effect of transition

Description: Report presents the results of experimental and theoretical research conducted on flow separation associated with steps, bases, compression corners, curved surfaces, shock-wave boundary-layer reflections, and configurations producing leading-edge separation. Results were obtained from pressure-distribution measurements, shadowgraph observations, high-speed motion pictures, and oil-film studies. The maximum scope of measurement encompassed Mach numbers between 0.4 and 3.6, and length Reynolds nu… more
Date: November 29, 1956
Creator: Chapman, Dean R.; Kuehn, Donald M. & Larson, Howard K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary investigation of Guy alloy as a turbojet-engine bucket material for use at 1650 degrees F

Description: As-cast buckets of Guy alloy, a cast nickel-base material, were run in a J33-9 turbojet engine for cycles of 15 minutes at rated speed and 5 minutes at idle speed. Stress rupture, impace and engine-performance data indicate that Guy alloy may be considered for bucket use at a temperature of 1650 degrees F. Ductility and impact strength of Guy alloy is limited but appears to be adequate for bucket applications.
Date: November 29, 1956
Creator: Signorelli, R. A.; Johnston, J. R. & Weeton, J. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Semigraphical Method for the Determination of the Rolling Characteristics of Rolleron-Equipped Missiles

Description: "A semigraphical analysis method has been devised to evaluate the effectiveness and dynamic stability of rolleron roll-rate dampers on missile configurations. The necessary charts, equations, and the analysis procedure have been presented. The greatest utility of these charts and of the method outlined is that, once a point on the charts has been established at a given flight condition, if the response is not acceptable than the necessary modifications to the parameters of the system are readil… more
Date: November 29, 1956
Creator: Nason, Martin L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Static lateral and directional stability and control characteristics of a 1/15-scale model of the Grumman F11F-1 airplane at Mach numbers of 1.41, 1.61, and 2.01: TED No. NACA DE 390

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the static lateral and directional stability and control characteristics of a scale model of the Grumman F11F-1 airplane at Mach numbers of 1.41, 1.61, and 2.01. The complete model and various combinations of component parts were tested as well as various configuration changes including modified bodies and vertical tails. Results regarding the static lateral and directional stability, lateral and dire… more
Date: November 29, 1956
Creator: Robinson, Ross B. & Driver, Cornelius
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Thermal Stability of Decaborane and of a Commercial Ethyl Decaborane (HEF-3) in the Range 202 Degrees to 252 Degrees C

Description: Report discussing an investigation of the thermal stabilities of a commercial grade of ethyl decaborane and decaborane at two temperatures. Equations developed from the results of the experiment are also provided. Ethyl decaborane was found to be more stable to pyrolysis than pentaborane but less stable than decaborane.
Date: November 29, 1956
Creator: McDonald, G. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of fuselage circumferential inlet location on diffuser-discharge total-pressure profiles at supersonic speeds

Description: An experimental investigation of the effect of angle of attack and inlet corrected air flow on diffuser-discharge total-pressure profiles of inlets located in various circumferential positions on a fuselage was conducted at supersonic speeds. Results indicated that the diffuser total-pressure profiles for a bottom inlet were least affected by angle of attack on distortion level was obtained with a side inlet. Variation in distortion for top inlets with angle of attack was confined to the superc… more
Date: October 29, 1956
Creator: Kremzier, Emil J. & Wasserbauer, Joseph F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of several design variables on internal performance of convergent-plug exhaust nozzles

Description: Numerous experiments were conducted to determine factors which affect the internal performance of convergent-plug exhaust nozzles. The results of these experiments, which include effects of such things as plug shape, nozzle inlet Mach number, and outer-shell characteristics, provide a basis for optimum desifn from the standpoint of weight and size. The results also show performance penalties which can result when the nozzle is too small.
Date: October 29, 1956
Creator: Krull, H. George; Beale, William T. & Schmiedlin, Ralph F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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