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Comparison of full-scale propellers having R.A.F.-6 and Clark Y airfoil sections

Description: In this report the efficiencies of two series of propellers having two types of blade sections are compared. Six full-scale propellers were used, three having R. A. F.-6 and three Clark Y airfoil sections with thickness/chord ratios of 0.06, 0.08, and 0.10. The propellers were tested at five pitch setting, which covered the range ordinarily used in practice. The propellers having the Clark Y sections gave the highest peak efficiency at the low pitch settings. At the high pitch settings, the pro… more
Date: October 8, 1930
Creator: Freeman, Hugh B.
Item Type: Refine your search to only Report
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Static, Drop, and Flight Tests on Musselman Type Airwheels

Description: The purpose of this investigation was to obtain quantitative information on the shock-reducing and energy-dissipating qualities of a set of 30 by 13-6 Musselman type airwheels. The investigation consisted of static, drop, and flight tests. The static tests were made with inflation pressures of approximately 0, 5, 10, 15, 20, and 25 pounds per square inch and loadings up to 9,600 pounds.
Date: October 8, 1930
Creator: Peck, William C. & Beard, Albert P.
Item Type: Refine your search to only Report
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Consolidation and shaping of boron ; summary of previous work

Description: From abstract: "The deposit on the rods is in the form of a brittle uneven tube which is cracked off and subsequently pulverized to a 200-mesh powder. This report is chiefly concerned with methods of consolidating this powder and shaping it into forms required, though it also discusses to some extent other methods of shaping boron or born-rich materials."
Date: October 8, 1945
Creator: Kamm, Robert L.
Item Type: Refine your search to only Report

Newsmap for the Armed Forces : Code for the Conquered

Description: Front: Text describes principal points which disestablish the Reich and eliminate its war-making powers Photograph: A group of men in uniform and in street dress stand in the foreground appearing to read the code for the conquered. Back: Illustration of a serviceman in a hand-held test tube is accompanied by text giving points about identifying and preparing to pick a civilian job after discharge from the service.
Date: October 8, 1945
Creator: [United States.] Army Service Forces. Army Information Branch.
Item Type: Refine your search to only Poster
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Flight and Test-Stand Investigation of High-Performance Fuels in Pratt & Whitney R-1830-94 Engines 4: Comparison of Cooling Characteristics of Flight and Test-Stand Engines

Description: "The cooling characteristics of three R-1830-94 engines, two of which were mounted in a test stand and the other in a B-24D airplane, were investigated and the results were compared. The flight tests were made at a pressure altitude of 7000 feet; the test-stand runs were made at ground-level atmospheric conditions. Three cooling runs were made for each engine: variable cooling-air pressure drop, variable carburetor-air flow, and variable fuel-air ratio" (p. 1).
Date: October 8, 1946
Creator: Dandois, Marcel & Werner, Milton
Item Type: Refine your search to only Report
open access

Estimation of Range of Stability Derivatives for Current and Future Pilotless Aircraft

Description: Memorandum presenting an analysis made of the probable range of the stability parameters of present and future missiles. Included is a short review of the dynamic theory and some of the factors and assumptions influencing the stability derivatives and equations of motion.
Date: October 8, 1947
Creator: Pitkin, Marvin & Ankenbruck, Herman O.
Item Type: Refine your search to only Report
open access

Investigation of Turbine of Mark 25 Torpedo Power Plant with Five Nozzle Designs

Description: "Efficiency investigations were made on the two-stage turbine from a Mark 25 aerial torpedo to determine the performance of the unit with five different turbine nozzles. The output of the turbine blades was computed by analyzing the windage and mechanical-friction losses of the unit. A method was developed for measuring the change in turbine clearances with changed operating conditions. The turbine was found to be most efficient with a cast nozzle having a sharp-edged inlet to the nine nozzle p… more
Date: October 8, 1947
Creator: Hoyt, Jack W. & Kottas, Harry
Item Type: Refine your search to only Report
open access

Some preliminary results in the determination of aerodynamic derivatives of control surfaces in the transonic speed range by means of a flush-type electrical pressure cell

Description: Report presenting the use of a flush-type electrical pressure cell for measuring rapidly changing aerodynamic forces on a fluttering control surface. The use of the cell is valuable for the measurement of the aerodynamic forces. Results regarding the individual cells, integrated results, resolution of aerodynamic moments, comparison of aerodynamic with inertia moments, and comparison of static and dynamic hinge moments are provided.
Date: October 8, 1948
Creator: Erickson, Albert L. & Robinson, Robert C.
Item Type: Refine your search to only Report
open access

Analytical Chemistry Division Quarterly Progress Report for Period Ending March 26, 1951

Description: Technical report covering experiments happening on the Analytical Chemistry Division's sites at the Oak Ridge National Laboratory. Includes information on ionic analyses, radio-chemical analyses, spectrochemical analyses, service analyses, inorganic preparations, analytical chemical control of homogeneous reactor solution, optical and electron microscopy, and service analyses for the period ending March 26, 1951. [From Abstract]
Date: October 8, 1951
Creator: Kelley, M. T. & Susano, C. D.
Item Type: Refine your search to only Report
open access

Damping in Roll of Rocket-Powered Test Vehicles Having Swept, Tapered Wings of Low Aspect Ratio

Description: "Flight tests of rocket-powered models have been conducted to determine the damping in roll of a group of swept, tapered wings designed for flight in the transonic speed region. The Mach number range of these tests was from approximately 0.7 to 1.4. The experimental damping in roll for all configurations was less than predicted by linearized theory throughout the Mach umber range of these tests. The only wing in this group that experienced an appreciable transonic lateral trim change was the on… more
Date: October 8, 1951
Creator: Sanders, E. Claude, Jr. & Edmondson, James L.
Item Type: Refine your search to only Report
open access

Derivation of the Equations of Motion of a Symmetrical Wing-Tip-Coupled Airplane Configuration With Rotational Freedom at the Junctures

Description: "The method of Lagrange multipliers is used to take account of the dynamic effects of the constraints at the wing tips when two identical airplanes are coupled to the wing tips of a "mother" airplane. The resulting equations of motion of this symmetrical configuration are derived for one, two, or three degrees of rotational freedom at each joint" (p. 1).
Date: October 8, 1951
Creator: Schy, Albert A.
Item Type: Refine your search to only Report
open access

Free-flight measurements at Mach numbers from 0.7 to 1.6 of some effects of airfoil-thickness distribution and trailing-edge angle on aileron rolling effectiveness and drag for wings with 0 and 45 degrees sweepback

Description: Report presenting the wing-aileron rolling effectiveness and drag for full-span sealed ailerons on untapered wings over a range of Mach numbers by using rocket-propelled test vehicles in free flight.
Date: October 8, 1951
Creator: Fields, E. M. & Strass, H. Kurt
Item Type: Refine your search to only Report
open access

Some Effects of Fuselage Interference, Wing Interference, and Sweepback on the Damping in Roll of Untapered Wings as Determined by Techniques Employing Rocket-Propelled Vehicles

Description: Report presenting an experimental investigation utilizing rocket propelled vehicles in free flight to determine some effects of fuselage interference, wing interference, and sweepback on the damping-in-roll characteristics of untapered wings with an aspect ratio of 3.7 and NACA 65A009 airfoil sections between a range of Mach numbers.
Date: October 8, 1951
Creator: Bland, William M., Jr. & Dietz, Albert E.
Item Type: Refine your search to only Report
open access

An analytical study of sideslip angles and vertical-tail loads in rolling pullouts as affected by some characteristics of modern high-speed airplane configurations

Description: From Introduction: "The rolling-pullout maneuver (any maneuver in which rolls occur during high g flight conditions) has been shown to be pertinent to design considerations from the standpoint of the loads produced on a vertical tail (refs. 1 to 3). In order to understand this problem better, the results of an analytical study of effects of large variations of some of the lateral-stability-derivative coefficients on the maximum angle of sideslip at first peak of its oscillation are presented in… more
Date: October 8, 1953
Creator: Stone, Ralph W., Jr.
Item Type: Refine your search to only Report
open access

Elastic Buckling Under Combined Stresses of Flat Plates With Integral Waffle-Like Stiffening

Description: Theory and experiment were compared and found in good agreement for the elastic Buckling under combined stresses of long flat plates with integral waffle-like stiffening in a variety of configurations. For such flat plates, 45deg waffle stiffening was found to be the most effective of the configurations for the proportions considered over the widest range of combinations of compression and shear.
Date: October 8, 1953
Creator: Dow, Norris F.; Levin, L. Ross & Troutman, John L.
Item Type: Refine your search to only Report
open access

Experimental Investigation of Several Water-Injection Configurations for Turbine-Blade Spray Cooling in a Turbojet Engine

Description: Memorandum presenting an investigation of water spray cooling of turbine rotor blades with a representative centrifugal-flow turbojet engine. Water injection from several stationary configurations was investigated in order to determine the most favorable configuration on an overall basis. Results regarding blade temperature distributions, cooling efficiencies of various configurations, rotor blades failures, rotor blade spray patterns, and overall comparison of injection configurations are prov… more
Date: October 8, 1953
Creator: Freche, John C. & McKinnon, Roy A.
Item Type: Refine your search to only Report
open access

Theoretical Calculations of the Stability Derivatives at Supersonic Speeds for a High-Speed Airplane Configuration

Description: "Theoretical calculations of the stability derivatives at supersonic speeds for a high-speed airplane configuration are presented. The range of Mach numbers considered includes those cases for which the wing and tail surfaces have subsonic leading edges, supersonic leading edges, and combinations of the two. The methods of analysis are discussed; these represent detailed consideration of the important effects and contributions of the various airplane components utilizing available theories and … more
Date: October 8, 1953
Creator: Margolis, Kenneth & Bobbitt, Percy J.
Item Type: Refine your search to only Report
open access

Use of Commercial Grade Methane in ASP Counting Instruments

Description: The gas commonly used in the chamber of the Simpson Proportional Alpha Counter (ASP) is the high grade, 99% pure methane. The cost of the gas has often raised the question of finding an adequate substitute and a number of substitutions have been attempted. Commercial methane has been substituted successfully for 99% pure methane and its use is recommended in ASP counters. Neither commercial nor technical methane caused any significant changes in instrument operation.
Date: October 8, 1953
Creator: Rasmussen, M. J.
Item Type: Refine your search to only Report
open access

Welded Closures for Fuel Elements

Description: From abstract: "The inert-gas metal-arc welding process was used to determine weldability studies of various aluminum alloys that are being considered for use as can materials. The solid-phase and induction welding processes were also investigated for making can closures."
Date: October 8, 1953
Creator: Sopher, R. P.; Martin, G. E.; Grable, G. B.; Voldrich, C. B.; Leatherman, A. F. & Todd, F. C.
Item Type: Refine your search to only Report
open access

Analysis of Wind-Tunnel Tests at Low Speeds of a Four-Engine Propeller-Driven Airplane Configuration Having a Wing With 40 Degrees of Sweepback

Description: Report presenting an investigation to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane with a 40 degree swept wing with an aspect ratio of 10. Results regarding components of the lift changes due to operating propellers, components of the pitching-moment changes due to operating propellers, effect of configuration changes on the pitching-moment characteristics of the model, stick-fixed longitudinal stability of the model, reduct… more
Date: October 8, 1954
Creator: Edwards, George G. & Buell, Donald A.
Item Type: Refine your search to only Report
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