National Advisory Committee for Aeronautics (NACA) - 13,786 Matching Results

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Analysis of Low-Temperature Nuclear-Powered Ramjet Missile for High Altitudes

Description: From Summary: "The reactor operating conditions were varied to enable selection of values giving a good compromise between low uranium investment and loss gross weight at each altitude and flight Mach number considered. The corresponding values of reactor and missile operating conditions are presented in the report."
Date: November 9, 1955
Creator: Rom, F. E. & Sams, E. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Design Variables on Performance of Mach 4.0 Hydrogen Expansion Engines

Description: Memorandum presenting performance calculations for hypothetical hydrogen expansion engines in which only a small part of the engine airflow passes through the heat exchanger. The flight path was representative of those for long-range, high-speed aircraft. Results regarding the off-design operation and engine performance are provided.
Date: July 22, 1958
Creator: Dugan, James F., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Analysis of Hydrogen-Rich Hypersonic Ramjet Operation

Description: Report discussing findings on net thrust, fuel flow, and related performance indices for hydrogen-rich operation of nacelle-type and submerged ramjet engines at various Mach numbers. Testing concluded that the system could be helpful in a flight path involving acceleration from low to high flight speeds. Some trends of the effect of the operation conditions are noted, but no conclusions are drawn because of the preliminary nature of the report.
Date: January 14, 1958
Creator: Breitwieser, Roland & Morris, James F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of Effect of Spike- Tip and Cowl-Lip Blunting on the Internal Performance of a Two-Cone Cylindrical-Cowl Inlet at Mach Number 4.95

Description: Memorandum presenting the effect of blunting on the internal performance of a two-cone inlet with an internally cylindrical cowl investigated experimentally at Mach number 4.95. Total-pressure-recovery and mass-flow data were obtained for a range of spike and cowl bluntness.
Date: September 23, 1958
Creator: Weston, Kenneth C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Synthesis and Hydrolysis-Rate Studies of Decaborane Derivatives

Description: Report discussing a series of experiments involving the reaction of water with decaborane and HEF-3, a boron fuel containing ethyldecaborane. The chemical properties of the hydrolysis reaction are described. Two isomers were also prepared to assist with the syntheses, and their melting points, molecular weights, and solubilities in certain solvents are included.
Date: October 8, 1957
Creator: Lucas, D. & Lipschitz, A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight, Analog-Simulator, and Analytical Studies of an Automatically Controlled Interceptor Which Uses a Bank-Angle-Error Computer for Lateral Commands

Description: Report presenting the tracking performance of an automatically controlled interceptor in which the deflection channel incorporated a bank-angle-error computer that commanded rolling velocities of the interceptor proportional to the computed bank-angle errors. Results regarding gravity terms included in bank-angle-error computation and a comparison of modified system using bank-angle-error computer with the prototype system are provided.
Date: August 11, 1958
Creator: Cheatham, Donald C. & Brissenden, Roy F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of Five Short Multielement Turbojet Combustors for Hydrogen Fuel in Quarter-Annulus Duct

Description: Report described five short multielement turbojet combustors for use with hydrogen fuel and their performance. Information about the combustion efficiency, temperature profiles, pressure loss, durability, and comparison with previous short combustors is included.
Date: July 22, 1958
Creator: Jones, Robert E. & Rayle, Warren D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Spike-Tip and Cowl-Lip Blunting on Inlet Performance of a Mach 3.0 External-Compression Inlet

Description: Report presenting an investigation of the effect of inlet component blunting on performance using an axisymmetric external-compression inlet in the supersonic wind tunnel. The investigation was carried out to determine the performance penalties associated with spike-tip and cowl-lip blunting. Results regarding the effect of rounding the spike tip on inlet performance, overall drag coefficients, flow distortion, and Schileren photographs are provided.
Date: September 23, 1958
Creator: Cubbison, R. W. & Samanich, N. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Transonic Flight Evaluation of the Effects of Fuselage Extension and Indentation on the Drag of a 60-Degree Delta Wing Interceptor Airplane

Description: Report presenting the lift and drag characteristics of a 60-degree delta-wing interceptor airplane with fuselage extension and indentation at a range of Mach numbers and altitudes. A comparison with a prototype airplane and a comparison of the flight results with the model tests are provided.
Date: September 26, 1957
Creator: Saltzman, Edwin J. & Asher, William P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Thermal System for Continuous Monitoring of Laminar and Turbulent Boundary-Layer Flows During Routine Flight

Description: Note presenting a thermal system that can be used to determine whether the boundary layer on a wing in flight is turbulent or laminar. Tests were made of the system in the low-turbulence pressure tunnel. Other instruments and materials that could be used to enhance the system are described.
Date: September 1957
Creator: Richardson, Norman R. & Horton, Elmer A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Systematic Wind-Tunnel Measurements on a Laminar Wing With Nose Flap

Description: "Results of measurements are given as a supplement to earlier tests for a laminar profile with nose flap; magnitude, form, and angle of attack of the flap were systematically changed. The experiments were carried out at an effective Reynolds number of 8.2 x 10(exp 5). A comparison with measurements on other profiles shows that the effect of a nose flap is essentially dependent upon magnitude of the nose radius coefficient of the profile" (p. 1).
Date: April 1947
Creator: Krueger, W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Wind-Tunnel Investigation of the Effect of Area Suction on the Laminar Boundary Layer Over an NACA 64A010 Airfoil

Description: Memorandum presenting a preliminary investigation made in the two-dimensional low-turbulence tunnel on an NACA 64A010 airfoil with permeable surfaces to obtain an indication of the stabilizing effect of area suction on the laminar boundary layer. Although the airfoil surface had many waves and irregularities of contour, the data corroborated qualitatively the theoretically predicted stabilizing effect of area suction on a smooth flat plate.
Date: April 26, 1948
Creator: Braslow, Albert L.; Visconti, Fioravante & Burrows, Dale L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of Boundary-Layer Suction Through Slots to Obtain Extensive Laminar Boundary Layers on a 15 Percent-Thick Airfoil Section at High Reynolds Numbers

Description: Memorandum presenting a two-dimensional wind-tunnel investigation to determine the extent to which boundary-layer removal through slots is effective as a means for maintaining extensive laminar layers at high Reynolds numbers. Results regarding drag, suction-flow and pressure-loss distribution, surface pressure distribution, lift, and difficulties encountered in obtaining extensive laminar flow are provided.
Date: June 23, 1952
Creator: Loftin, Laurence K., Jr. & Horton, Elmer A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical Investigation of Drag Reduction in Maintaining the Laminar Boundary Layer by Suction

Description: "Maintenance of a laminar boundary layer by suction was suggested recently to decrease the friction drag of an immersed body, in particular an airfoil section. The present treatise makes a theoretical contribution to this question in which, for several cases of suction and blowing, the stability of the laminar velocity profile is investigated. Estimates of the minimum suction quantities for maintaining the laminar boundary layer and estimates of drag reduction are thereby obtained" (p. 1).
Date: June 1947
Creator: Ulrich, A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Further Experimental Studies of Area Suction for the Control of the Laminar Boundary Layer on a Porous Bronze NACA 64A010 Airfoil

Description: Note presenting a low-turbulence wind-tunnel investigation of an NACA 64A010 airfoil with a porous surface to determine the reduction in section total-drag coefficient that might be obtained at large Reynolds numbers by the use of area suction. This report primarily deals with additional tests of the same airfoil model equipped with a porous skin of lower porosity.
Date: May 1950
Creator: Braslow, Albert L. & Visconti, Fioravante
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental and Theoretical Studies of Area Suction for the Control of the Laminar Boundary Layer on a Porous Bronze NACA 64A010 Airfoil

Description: Note presenting a low-turbulence wind tunnel investigation of an NACA 64A010 airfoil with a porous surface of sintered bronze to determine the reduction in section drag coefficient that might be obtained at large Reynolds numbers by use of suction to produce continuous inflow through the surface of the model. Results regarding the uncompartmented model, compartmented model, observations on stability of laminar boundary layer, and theoretical calculations are provided.
Date: July 1949
Creator: Burrows, Dale L.; Braslow, Albert L. & Terervin, Neal
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Tests of the High-Speed Performance of a P-51B Airplane (AAF No. 43-12105)

Description: Report discussing testing to check the improvement of 3 or 4 miles per hour in the maximum speed of the P-51B airplane as a result of sealing the wing-gun access doors and flap-spar lightening holes. Large variations in speed were observed during testing, so additional testing and analysis was carried out to determine the effects of various factors that were suspected of contributing to the inconsistency of the plane's performance.
Date: December 18, 1944
Creator: Voglewede, T. J. & Danforth, E. C. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Boundary-Layer Measurements on Several Porous Materials With Suction Applied

Description: Memorandum presenting the boundary-layer velocity profiles were measured on ten samples of various porous materials and on impervious aluminum plate mounted flush with the inner surface of the side wall of a small wind tunnel. Suction was applied to the back side of the porous test materials through a 4-inch-square opening. Results regarding measurements on the impervious plate and measurements on porous materials without suction and with suction are provided.
Date: June 18, 1952
Creator: McCullough, George B. & Gambucci, Bruno J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Investigation of Boundary-Layer Transition and Profile Drag of an Experimental Low-Drag Wing Installed on a Figher-Type Airplane

Description: Report presenting a boundary-layer-transition and profile-drag investigation conducted on an experimental low-drag wing installed on a P-47 airplane designated the XP-47F. Measurements were made at a section outside the propeller slipstream with smooth and with standard camouflage surfaces and on the upper surface of a section in the propeller slipstream with the surface smoothed. Results regarding the right wing section outside the slipstream and left wing section in the propeller slipstream a… more
Date: April 1945
Creator: Zalovcik, John A. & Skoog, Richard B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine 2: Rotor Blades With 15 Fins in Cooling-Air Passages

Description: Report presenting an investigation to experimentally determine the effectiveness of air-cooling several configurations of turbine blades in a turbojet engine. The results of the second blade configuration, which consists of a hollow blade shell with 15 fins inserted, are provided. The factors involved in the design of the blade configuration are also included.
Date: August 1950
Creator: Hickel, Robert O. & Ellerbrock, Herman H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Radiant Heat Transfer From Flames in a Single Tubular Turbojet Combuctor

Description: Memorandum presenting an investigation to determine the energy transfer by thermal radiation from the flame of a single tubular turbojet-engine combustor to the combustor liner. The effects of variations in combustor inlet-air pressure, fuel-air ratio, and air mass flow on the transfer of radiant energy were studied.
Date: August 19, 1952
Creator: Topper, Leonard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine: 1: Rotor Blades With 10 Tubes in Cooling-Air Passages

Description: Report presenting an investigation to experimentally determine the effectiveness of air cooling several turbine-blade configurations in a turbojet engine. The results obtained with the first configuration, which was a hollow blade shell with 10 tube inserts, are presented. A description of factors leading to the design are provided as well as the correlated cooled-blade temperatures, solid-blade temperatures, cooling-air-temperature increase through radial passages, and blade failure are provid… more
Date: July 30, 1950
Creator: Ellerbrock, Herman H., Jr. & Stepka, Francis S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation at Mach Number 1.91 of Spreading Characteristics of Jet Expanding From Choked Nozzles

Description: Report presenting an investigation at Mach number 1.91 to determine the gross spreading characteristics of jets expanding from convergent and convergent-divergent nozzles using total-temperature surveys. Results regarding the preliminary development and jet spreading characteristics of the different types of nozzles are provided.
Date: February 11, 1952
Creator: Rousso, Morris D. & Baughman, L. Eugene
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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