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Determination of Rate, Area, and Distribution of Impingement of Waterdrops on Various Airfoils From Trajectories Obtained on the Differential Analyzer
"The trajectories of waterdrops in air flowing over airfoils are determined for three airfoil - angle-of-attack combinations using the differential analyzer to solve the differential equations of motion of the waterdrops. From these trajectories the rate of water impingement, the area of impingement, and the distribution of impingement are determined as functions of two dimensionless moduli. Comparisons are made of the rate of water impingement on these airfoils and the rate of water impingement on cylinders" (p. 1).
Date:
February 16, 1949
Creator:
Guibert, A. G.; Janssen, E. & Robbins, W. M.
System:
The UNT Digital Library
Determination of rate, area, and distribution of impingement of of waterdrops on various airfoils from trajectories obtained on the differential analyzer
From Summary: "The trajectories of waterdrops in air flowing over airfoils are determined for three airfoil-angle-of-attack combinations using the differential analyzer to solve the differential equations of motion of the waterdrops. From these trajectories the rate of water impingement, the area of impingement, and the distribution of impingement are determined as functions of two dimensionless moduli. Comparisons are made of the rate of water impingement on these airfoils and the rate of water impingement on cylinders."
Date:
February 16, 1949
Creator:
Guibert, A. G.; Janssen, E. & Robbins, W. M.
System:
The UNT Digital Library
A review of instruments developed for the measurement of the meteorological factors conductive to aircraft icing
Report presenting a review of the status of instruments suitable for the measurement of the meteorological factors conducive to aircraft icing. Nine instruments which appear to be the most promising for obtaining meteorological data are discussed and recommendations for their continued use and development are provided.
Date:
April 26, 1949
Creator:
Jones, Alun R. & Lewis, William
System:
The UNT Digital Library
An Electric Thrust Meter Suitable for Flight Investigation of Propellers
A lightweight instrument that utilizes resistance-wire electric strain gases to measure propeller-shaft thrust has been developed. A wind-tunnel investigation on a propeller installed, on a single-engine pursuit airplane showed that the instrument gave a reliable indication of propeller-shaft thrust to an accuracy of +/-2 percent within its calibrated range. No attempt was made to determine the relation of indicated shaft thrust to net propeller thrust.
Date:
May 9, 1949
Creator:
Perkins, Porter J., Jr. & Millenson, Morton B.
System:
The UNT Digital Library
Investigation of the Kingfisher XAUM-2 Flying Torpedo in the Langley Full Scale Tunnel, TED No. NACA DE 327
Report presenting an investigation of a model of the Kingfisher XAUM-2 flying torpedo to determine the pressure recoveries within the jet engine nacelle and to determine the effects of several changes in model configuration on the aerodynamic characteristics of the model. The effectiveness of elevons and tabs as control devices was also investigated.
Date:
October 6, 1949
Creator:
Cocke, Bennie W. & Barnett, U. Reed
System:
The UNT Digital Library
Downwash in Vortex Region Behind Trapezoidal-Wing Tip at Mach Number 1.91
Report presenting the results of an experimental investigation to determine the downwash in the region of the trailing vortex behind a trapezoidal-wing tip in a supersonic stream. Results regarding the downwash at spanwise stations, downwash at chordwise stations, and wake survey are provided.
Date:
November 10, 1949
Creator:
Cummings, J. L.; Mirels, H. & Baughman, L. E.
System:
The UNT Digital Library
Wing-tunnel investigation at low transonic speeds of the effects of number of wings on the lateral-control effectiveness of an RM-5 test vehicle
Report presenting an investigation to determine the effects of number of wings on the aileron rolling effectiveness of an RM-5 test vehicle using the free-rolling wind-tunnel testing technique through a speed range to Mach number 0.9. The wings tested had neither taper nor sweepback and were equipped with full-span 20-percent-chord sealed and faired ailerons. Results indicated that increasing the number of wings resulted in a decrease in rolling effectiveness so that results obtained from the test of the three-wing model were closer to conventional-airplane-configuration results than the four-wing data.
Date:
November 29, 1949
Creator:
Johnson, Harold S.
System:
The UNT Digital Library
Spin-Tunnel Investigation of the Jettisoning of External Fuel Tanks in Spins
"A spin-tunnel investigation has been made to determine the probability of external fuel tanks striking an airplane after being jettisoned in a spin. The investigation showed that for straight-wing fighter-type designs in any case in which jettisoning of tanks in a spin might aid spin recovery the tanks would probably clear all parts of the airplane" (p. 1).
Date:
November 30, 1949
Creator:
Berman, Theodore
System:
The UNT Digital Library
Analytical determination of effect of water injection on power output of turbine-propeller engine
From Introduction: "Water injection at the compressor inlet has been successfully used to increase the thrust of turbojet engines. References 1 and 2 indicate that the sea-level static thrust of a centrifugal-flow-type turbojet engine may be increased about 25 percent by use of liquid injection. Reference 3 indicates that greater thrust augmentation is possible at a compressor pressure ratio of 11 than of 4."
Date:
November 3, 1949
Creator:
Ross, Albert O. & Huppert, Merle C.
System:
The UNT Digital Library
Comparative Tests of the Rolling Effectiveness of Constant-Chord, Full-Delta, and Half-Delta Ailerons on Delta Wings at Transonic and Supersonic Speeds
Report presenting comparative tests of the rolling power of plain constant-chord, full-delta, and half-delta ailerons on delta wings with varying degrees of sweepback were tested on rocket-propelled test vehicles. Results regarding the effect of leading-edge sweepback, a comparison of rolling effectiveness, and comparison with theory are provided.
Date:
December 12, 1949
Creator:
Sandahl, Carl A. & Strass, H. Kurt
System:
The UNT Digital Library
Low-Speed Investigation of Deflectable Wing-Tip Ailerons on an Untapered 45 Degrees Sweptback Semispan Wing With and Without an End Plate
Report presenting a low-speed wind-tunnel investigation to determine the characteristics of deflectable wing-tip ailerons on an untapered 45 degree sweptback semispan wing. Ailerons with triangular and parallelogram plan forms with a maximum chord of 0.625 wing chord and a flat-plat profile were investigated. The aerodynamic characteristics in pitch and lateral control characteristics are included.
Date:
December 14, 1949
Creator:
Fischel, Jack & Watson, James M.
System:
The UNT Digital Library
An Analysis of Airspeeds Attained by a Douglas DC-4 Airplane in Commercial Operations During the Early Months of 1947
Report presenting airspeed and altitude data for nonscheduled cargo operations of a Douglas DC-4 airplane between Seattle, Washington and Alaska during February and March of 1947 to determine the probability of reaching or exceeding given values of airspeed and Mach number. The total probability of exceeding a placard never-exceed speed of 266 mph depends primarily on exceeding the speed in descent. The probability was found to be about once in 100 hours of descent or once in 1000 hours of general flying time.
Date:
October 6, 1949
Creator:
Steiner, Roy
System:
The UNT Digital Library
Two-Dimensional Wind-Tunnel Investigation of Two NACA 7-Series Type Airfoils Equipped With a Slot-Lip Aileron, Trailing-Edge Frise Aileron, and a Double Slotted Flap
Report presenting a wind-tunnel investigation of two NACA 7-series type airfoils, one with 17.7-percent chord thickness and one with 15.4-percent chord thickness, each quipped with a 30-percent-airfoil-chord double slotted flap, a slot-lip aileron, and a trailing-edge Frise aileron with two amounts of overhang balance. Measurements of airfoil lift and drag, Frise aileron hinge moment, and slot-lip aileron hinge moment were obtained through a large range of deflection of flap, Frise aileron, and slot-lip aileron and section angle of attack. Satisfactory lateral control can be obtained by using this combination of airfoils, flaps, and ailerons.
Date:
March 28, 1949
Creator:
Braslow, Albert L. & Visconti, Fioravante
System:
The UNT Digital Library
Aerodynamic characteristics of a flying-boat hull having a length-beam ratio of 15 and a warped forebody
From Introduction: "The results of two phases of this investigation, presented in references 1 and 2, have indicated possible ways of reducing hull drag without causing large changes in aerodynamic stability and hydrodynamic performance."
Date:
February 11, 1949
Creator:
MacLeod, Richard G.
System:
The UNT Digital Library
Preliminary full-scale investigation of a 1/3-scale model of a convertible-type airplane
Report presenting the results of a preliminary investigation of a scale model of a convertible-type airplane in the full-scale tunnel. The maximum lift and stalling characteristics of several configurations, the longitudinal stability characteristics, and the effectiveness of the control surfaces with the propellers removed are provided. Results regarding the propulsive characteristics, and effect of propeller operation on the lift and static thrust of the model propellers are also provided.
Date:
June 7, 1949
Creator:
Lange, Roy H.; Cocke, Bennie W., Jr. & Proterra, Anthony J.
System:
The UNT Digital Library
Longitudinal Stability and Control Characteristics of a Semispan Wind-Tunnel Model of a Tailless Airplane and a Comparison With Complete-Model Wind-Tunnel Tests and Semispan-Model Wing-Flow Tests
Report presenting an investigation of a model of a tailless airplane in a high speed tunnel at a range of Mach numbers. Results are compared to those obtained from a sting-mounted model tested in the same tunnel and a semispan model tested with the wing-flow method. Information regarding basic aerodynamic characteristics, spoiler controls, lift characteristics, drag characteristics, pitching moment at zero lift, and stability and control is provided.
Date:
October 10, 1949
Creator:
Goodson, Kenneth W. & King, Thomas J., Jr.
System:
The UNT Digital Library
Comparison of performance of AN-F-58 and AN-F-32 fuels in J33-A-23 turbojet engine
Report presenting an investigation using a 4600 pound-thrust turbojet engine as part of a program to determine the comparative performance of fuels conforming to specifications AN-F-58 and AN-F-32. Results regarding the altitude performance, altitude low-speed blow-out limits, idling limits of fuel-metering control, altitude windmilling starts, carbon-deposition rates, and iron oxide contamination are provided.
Date:
June 2, 1949
Creator:
Wilsted, H. D. & Armstrong, J. C.
System:
The UNT Digital Library
Aerodynamic characteristics of a wing with quarter-chord line swept back 35 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section: Transonic-bump method
From Introduction: "This paper presents the results of the investigation of wing-alone and wing-fuselage combinations employing a wing with the quarter-chord line swept back 35^o, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section."
Date:
April 21, 1949
Creator:
Sleeman, William C., Jr. & Becht, Robert E.
System:
The UNT Digital Library
Low-Speed Investigation of Aileron and Spoiler Characteristics of a Wing Having 42 Degrees Sweepback of the Leading Edge and Circular-Arc Airfoil Sections at Reynolds Numbers of Approximately 6.0 X 10(Exp 6)
Report presenting a low-speed investigation to determine the effectiveness of a conventional aileron and various spanwise spoiler arrangements on a 42 degree sweptback wing. The rolling-moment characteristics of the aileron and the spoilers, as well as the aileron hinge-moment, normal-force, and balance-chamber pressure characteristics were determined for a plain wing and a wing equipped with several high-lift and stall-control devices.
Date:
March 10, 1949
Creator:
Spooner, Stanley H. & Woods, Robert L.
System:
The UNT Digital Library
Measurements of Aileron Effectiveness of Bell X-1 Airplane Up to a Mach Number of 0.82
"Abrupt, rudder-fixed aileron rolls have been made with the Bell X-1 airplane having a 10-percent-thick wing in glides to a Mach number of 0.82 at about 30,000 feet pressure altitude. Aileron movements were between one-fourth and one-half of full deflection. These aileron rolls indicate that Mach number has little effect on the aileron effectiveness up to a Mach number of 0.82" (p. 1).
Date:
June 20, 1949
Creator:
Drake, Hubert M.
System:
The UNT Digital Library
Wind-tunnel investigation of transonic aileron flutter
Report presenting a partial-span wing tested to determine the cause of a flutter which had occurred in high-speed flight. Changes were made to the wing stiffness, location of the center of gravity of the wing, and the mass balance of the aileron. Results regarding the effect of wing changes on flutter, effect of aileron changes on flutter, shock-wave study, and static aerodynamic coefficients are provided.
Date:
June 9, 1949
Creator:
Erickson, Albert L. & Mannes, Robert L.
System:
The UNT Digital Library
Aerodynamic characteristics of a 6-percent-thick symmetrical double-wedge airfoil at transonic speeds from tests by the NACA wing-flow method
From Introduction: "The investigation covered a range of Mach numbers from 0.66 to 1.12 and included measurements of angle of attack, pitching moment, normal force, and chord force. The drag at zero lift obtained in this investigation was reported in reference 1, but without the correction for tare of the end plate."
Date:
March 4, 1949
Creator:
Lina, Lindsay J.
System:
The UNT Digital Library
Investigations of an Annular Diffuser-Fan Combination Handling Rotating Flow
Memorandum presenting an investigation of two annular diffusers of different conical angles of expansion but constant outer diameters with rotating flow behind a fan. The performance characteristics are determined and the rotational-kinetic-energy effects on the overall energy transformation are observed over a range of inlet mach numbers from 0.1 to 0.44 and angles of flow up to 28 degrees.
Date:
April 25, 1949
Creator:
Schwartz, Ira R.
System:
The UNT Digital Library
Hydrodynamic characteristics of a swept planing-tail hull
Report presenting the hydrodynamic characteristics of a swept planing-tail hull as determined by water tank testing. The hull shape was based on results from previous testing indicating that symmetrical airfoil sections and slender boom-like afterbodies lower the drag. Results regarding spray characteristics, take-off stability and trims, landing stability, resistance, and directional stability are presented.
Date:
September 12, 1949
Creator:
McKann, Robert E.; Coffee, Claude W. & Arabian, Donald D.
System:
The UNT Digital Library