UNT Libraries Government Documents Department - 243 Matching Results

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Tests of a 1/40-Scale Wing-Hull Model and a 1/10-Scale Float-Strut Model of the Hughes-Kaiser Cargo Airplane in the Two-Dimensional Low-Turbulence Pressure Tunnel

Description: Report presenting aerodynamic and hydrodynamic tests of a 1/10-scale wing-hull model and a 1/10-scale float-strut model of the proposed arrangement of the Hughes-Kaiser cargo airplane. The aerodynamic tests were made primarily to study the drag characteristics of these models as originally designed and to determine how the design could be improved. Results regarding the wing-hull model and float-strut model are provided.
Date: September 1943
Creator: Fullmer, Felicien F., Jr.
Item Type: Refine your search to only Report
open access

Tests of a dynamic model in NACA tank number 1 to determine the effect of length of afterbody, angle of afterbody keel, gross load, and a pointed step on landing and planning stability

Description: Report presenting testing in tank no. 1 to determine the effect of length of afterbody, angle of afterbody keel, and gross load on the limits of stable trims and landing characteristics of a model of a flying boat with conventional steps. The studies were made with four lengths of afterbody, four angles of afterbody keel, and five gross loads. Results regarding the trim limits of stability and landing stability are provided.
Date: March 1943
Creator: Land, Norman S. & Lina, Lindsay J.
Item Type: Refine your search to only Report
open access

Tests of Exhaust Propulsion Nozzles

Description: "The thrust produced by a variety of exhaust stacks and nozzles, and the effect of these stacks and nozzles on the power of a single-cylinder R-2800 engine were investigated over a wide range of engine speeds and manifold pressures in a series of tests in the Pratt & Whitney experimental test department. From the data obtained it is possible to estimate the optimum form of nozzles and the available thrust for airplanes fitted with R-2800 engines under sea-level conditions" (p. 1).
Date: May 1943
Creator: Campbell, Paul J.
Item Type: Refine your search to only Report
open access

Tests of Inverted Spins in the NACA Free-Spinning Tunnels

Description: "Report discusses the results of inverted-spin tests in 44 airplane models in the NACA free-spinning tunnel. Spins were normally steep and recovery by rudder reversal was generally rapid. Pulling the stick back, deflecting ailerons and rudder together, and crossing them all had an effect on the amount of spin encountered and ease of recovery from spin" (p. 1).
Date: December 1943
Creator: MacDougall, George F., Jr.
Item Type: Refine your search to only Report
open access

Theoretical Analysis of the Lateral Stability of a Glider Towed by Twin Parallel Towlines

Description: Report discusses a theoretical analysis of the lateral stability characteristics of a glider towed by two parallel towlines, which was correlated with previously reported dynamic flight testing. The glider appears to possess sufficient stability for satisfactory pilotless towed flight. The main factors affecting stability were the dihedral angle of the glider and the length of the towlines.
Date: November 1943
Creator: Pitkin, Marvin & McKinney, Marion O., Jr.
Item Type: Refine your search to only Report
open access

A Theoretical Investigation of the Lateral Oscillations of an Airplane With Free Rudder With Special Reference to the Effect of Friction

Description: Report presenting charts showing the variation in dynamic stability with the rudder hinge-moment characteristics. A stabilizing rudder floating tendency combined with a high degree of aerodynamic balance is shown to lead to oscillations of increasing amplitude.
Date: March 1943
Creator: Greenberg, Harry & Sternfield, Leonard
Item Type: Refine your search to only Report
open access

Theory and preliminary flight tests of an all-movable vertical tail surface

Description: Report presenting flight testing of an improved type of all-movable tail surface. The particular arrangement tested provides control-free stability and a stable variation of the control forces during maneuvers. Results regarding rudder effectiveness, directional stability, rudder-free lateral motion, and rudder-free turns are provided.
Date: January 1943
Creator: Jones, Robert T. & Kleckner, Harold F.
Item Type: Refine your search to only Report
open access

Theory of Mechanical Oscillations of Rotors With Two Hinged Blades

Description: Report discusses an investigation into the mechanical stability of a rotor with two vertically hinged blades mounted on symmetrical supports of equal stiffness and mass. Information about the instability regions and effect of damping is included. The two-blade rotor was found to have two shaft-critical speeds at which instability can occur as well as a second region at which self-excited vibrations occur.
Date: September 1943
Creator: Feingold, Arnold M.
Item Type: Refine your search to only Report
open access

Theory of Self-Excited Mechanical Oscillations of Hinged Rotor Blades

Description: "Vibrations of rotary-wing aircraft may derive their energy from the rotation of the rotor rather than from the air forces. A theoretical analysis of these vibrations is described and methods for its application are explained herein" (p. 1). Information about self-excited speed range and shaft-critical speed are provided for any rotor with more than two blades.
Date: July 1943
Creator: Coleman, Robert P.
Item Type: Refine your search to only Report
open access

The Use of a Retractable Planing Flap Instead of a Fixed Step on a Seaplane

Description: Report presents and discusses the improvements in hydrodynamic and aerodynamic performance of a seaplane with a retractable planing flap instead of a conventional main step. A type of flap that could be used is described and tested for hydrodynamic stability. Results regarding the trim limits of stability, limiting positions of the center of gravity, and skipping are provided.
Date: May 1943
Creator: Benson, James M. & Lina, Lindsay J.
Item Type: Refine your search to only Report
open access

Use of Stagnation Temperature in Calculating Rate of Heat Transfer in Aircraft Heat Exchangers

Description: "Theoretical and experimental investigations of the effect of frictional heat on the rate of heat transmission at high fluid velocities are briefly reviewed. On the basis of these investigations, calculations are made which show that the use of the stagnation temperature of the cooling air as the effective temperature for heat transfer in an aircraft heat exchanger is sufficiently accurate" (p. 1).
Date: October 1943
Creator: Wood, George P.
Item Type: Refine your search to only Report
open access

Vibration Surveys of the P-40 Rudder and Fin-Rudder Assembly

Description: "The following surveys on the vibration response of the P-40 rudder and fin-rudder assembly were conducted during the fall of 1942 for the purpose of obtaining information on the flutter characteristics of high-speed airplanes of known performance. The tests on the rudder alone were made with the rudder suspended in a floating condition; the tests on the fin-rudder unit were made with the fin rigidly fastened to a concrete base" (p. 1). A variety of figures and diagrams for the assembly are pro… more
Date: April 1943
Creator: Theodorsen, Theodore & Regier, Arthur A.
Item Type: Refine your search to only Report
open access

Vibration Surveys of the P-47-B Rudder and Fin-Rudder Assembly

Description: Report presenting a study of the flutter characteristics of the P-47 tail assembly, which included replacing the original fabric-covered rudder with a metal-covered rudder and reinforcing the fin. Figures are provided for different configurations and the cycles per second under the same conditions are provided.
Date: April 1943
Creator: Theodorsen, Theodore & Regier, Arthur A.
Item Type: Refine your search to only Report
open access

Water tolerance of aviation gasoline containing xylidines

Description: Report presenting investigations to determine the effect of xylidines on the saturation concentration of water in aviation gasoline. The saturation concentration of water in gasoline containing 0, 1, and 3 percent xylidines was determined using fresh water at two temperatures and sea water at one temperature.
Date: July 1943
Creator: Revilock, Joseph & Olson, Walter T.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of a Full-Span Retractable Flap in Combination With Full-Span Plain and Internally Balanced Ailerons on a Tapered Wing

Description: Report discusses the results of an investigation into a full-span retractable flap in combination with a full-span plain and internally balanced ailerons on a tapered wing of a typical fighter airplane.The flap was designed to improve lateral control during high lifts for landing and take-off. The effects on the maximum life coefficient, aileron effectiveness, estimated rates of roll, and stick forces are provided.
Date: August 1943
Creator: Rogallo, F. M.; Lowry, John G. & Fischel, Jack
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of a Low-Drag Airfoil Section with a Double Slotted Flap

Description: From Summary: "Tests were made of an 0.309-chord double-slotted flap on an NACA 65, 3-118, a equals 1.0 airfoil section to determine drag, lift, and pitching-moment characteristics for a range of flap deflections. Results indicate that combination of a low-drag airfoil and a double-slotted flap, of which the two parts moved as a single unit, gave higher maximum lift coefficients than have been obtained with plain, split, or slotted flaps on low-drag airfoils. Pitching moments were comparable to… more
Date: September 1943
Creator: Bogdonoff, Seymour M.
Item Type: Refine your search to only Report
open access

Wind-tunnel investigation of a plain aileron with thickened and beveled trailing edges on a tapered low-drag wing

Description: Report presenting an investigation in the 7- by 10-foot tunnel of various modifications of the trailing-edge portion of a 0.20-chord plain aileron on a partial-span model of a tapered low-drag wing. The modifications tested included various amounts of symmetrical and unsymmetrical thickening and beveling of the aileron trailing edge. Results regarding coefficients and corrections, characteristics with ailerons neutral, characteristics with ailerons deflected, aileron trim characteristics, and e… more
Date: January 1943
Creator: Purser, Paul E. & McKee, John W.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of a Plain Aileron with Various Trailing-Edge Modifications on a Tapered Wing 3: Ailerons with Simple and Spring-Linked Balancing Tabs

Description: Aerodynamics data are obtained for the design of linked balancing tabs and effect of varied tab span and location to produce suitable lateral control characteristics with reasonable stick pressures for high-speed aircraft. Simple and spring-linked balancing tabs may considerably reduce control pressures if aileron system is designed for low maximum aileron deflection. Spring-linked tabs also decrease variation of stick pressure with speed and impart better controlllability at low speeds.
Date: January 1943
Creator: Purser, Paul E. & Rogallo, F. M.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of an NACA 23012 Airfoil With a 0.30-Airfoil-Chord Double Slotted Flap

Description: Report discusses the results of testing of flap position and deflection on the aerodynamic characteristics of a NACA 23012 airfoil with a double slotted flap with a chord 30 percent of the airfoil chord. The maximum lift coefficient, profile-drag coefficients, pitching-moment coefficients, lift, and drag are provided at several positions of the flap. The results were also compared to previous testing on several flap configurations.
Date: December 1943
Creator: Purser, Paul E.; Fischel, Jack & Riebe, John M.
Item Type: Refine your search to only Report
open access

Wind Tunnel Investigation of Control-Surface Characteristics 11: Various Large Overhang and Internal-Type Aerodynamic Balances for a Straight- Contour Flap on the NACA 0015 Airfoil

Description: Report presenting force-test measurements in two-dimensional flow in the 4- by 6-foot vertical tunnel to determine the characteristics of several different shaped overhang-type aerodynamic balances applied to a straight-contour flap mounted on an NACA 0015 airfoil. The flap with blunt-nose overhang was overbalanced throughout certain ranges of flap deflection. Results regarding precision, lift, flap hinge moments, pitching moment, and drag are provided.
Date: January 1943
Creator: Sears, Richard I. & Hoggard, H. Page, Jr.
Item Type: Refine your search to only Report
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