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Wind-Tunnel Investigation at Low Speed of a Wing Having 63 Degree Sweepback and a Drooped Tip
From Summary: "The results of force tests made at low speed are presented to show the effect of longitudinal static stability produced by drooping the tip of a 63 degree sweptback wing. Five semispan wing models were tested: two incorporated curved drooped tips, two with abruptly drooped tips, and one without droop. The most favorable stability characteristics were measured for a model with an abruptly drooped tip, a fence, and a leading-edge flap; however, the use of these same auxiliary devices on the undrooped wing was nearly as effective."
Date:
April 7, 1955
Creator:
Blackaby, James R.
System:
The UNT Digital Library
Component Operating Trends During Acceleration and Deceleration of Two Hypothetical Two-Spool Turbojet Engines
Memorandum presenting an investigation of the compressor and turbine operating trends during acceleration and deceleration of two hypothetical two-spool turbojet engines. The two engines have the same component performance maps but the arbitrarily specified ratio of outer- to inner-spool moment of inertia for the second engine is 4 times that specified for the first engine. Results regarding the acceleration characteristics and deceleration characteristics are provided.
Date:
April 21, 1955
Creator:
Dugan, James F., Jr.
System:
The UNT Digital Library
An experimental investigation of two methods for reducing transonic drag of swept-wing and body combinations
Report presenting an investigation of a wing swept back 35 degrees in combination with one basic body and three modified bodies at a range of Mach numbers from 0.60 to 1.20. Results regarding force studies and pressure studies are provided. The bodies modified according to the Kuchenmann ring-vortex method resulted in superior aerodynamic characteristics except with regard to zero-lift drag at high supersonic Mach numbers.
Date:
April 29, 1955
Creator:
McDevitt, John B.
System:
The UNT Digital Library
Lift, drag, and static longitudinal stability characteristics of four airplane-like configurations at Mach numbers from 3.00 to 6.28
Report presenting lift, drag, and pitching-moment coefficients, lift-drag ratios, and center-of-pressure positions for four airplane-like configurations determined from tests at a range of Mach numbers and angles of attack. The wings and nose shapes were modified for each of the configurations.
Date:
April 25, 1955
Creator:
Neice, Stanford E.; Wong, Thomas J. & Hermach, Charles A.
System:
The UNT Digital Library
Effect of Design Compressor Pressure Ratio on Performance of Hypothetical Two-Spool Nuclear-Powered Turbojet Engines
Memorandum presenting hypothetical two-spool nuclear-powered turbojet engines with sea-level static design compressor total-pressure ratios of 20, 15, and 9 and total-pressure losses between the inner-spool compressor exit and turbine inlet of 10 and 30 percent. Results regarding compressor operating lines, gas-generator performance, engine performance, and some general remarks are provided.
Date:
April 10, 1955
Creator:
Dugan, James F., Jr.
System:
The UNT Digital Library
Flight investigation of pentaborane fuel in 9.75-inch-diameter ram-jet engine with downstream fuel injection
Report presenting a flight test of pentaborane fuel in an air-launched ramjet engine with a design free-stream Mach number of 1.8. The ramjet used in the investigation had a revised spray bar-flameholder configuration. Results regarding propulsive thrust and propulsive-thrust specific fuel consumption are provided.
Date:
April 22, 1957
Creator:
Disher, John H. & Jones, Merle L.
System:
The UNT Digital Library
Effect on the low-speed aerodynamic characteristics of a 49 degree sweptback wing having an aspect ratio of 3.78 of blowing air over the trailing-edge flap and aileron
Report presenting an investigation in the full-scale tunnel to determine the effects on the aerodynamic characteristics of a 49.1 degree sweptback wing of blowing a high-energy stream of air over a trailing-edge flap and an aileron. The results indicated that significant increases in lift coefficient and an improvement in aileron effectiveness may be obtained by the blowing method of boundary-layer control.
Date:
April 23, 1954
Creator:
Whittle, Edward F., Jr. & Lipson, Stanley
System:
The UNT Digital Library
Investigation of the aerodynamic and icing characteristics of a recessed fuel cell vent assembly 3: NACA flush-inlet-type vent
An investigation conducted in the icing research tunnel to determine aerodynamic and icing characteristics of two flush-inlet-type fuel cell vent installations. The vent tubes were mounted in two different locations in the two installations. The vents were aerodynamically investigated to obtain vent-tube static-pressure differentials and pressure surveys as a function of tunnel-air velocity and angle of attack.
Date:
April 23, 1948
Creator:
Ruggeri, Robert S.
System:
The UNT Digital Library
Pressure recovery at supersonic speeds through annular duct inlets situated in a region of appreciable boundary layer 1: addition of energy to the boundary layer
Report presenting a model with a nozzle upstream of an annular duct inlet for the purpose of ejecting high-velocity air into the boundary layer of the flow along the forebody tested between Mach numbers of 1.36 and 2.01. Results wind-tunnel data, equivalent pressure recovery, and scale effects are provided.
Date:
April 1, 1948
Creator:
Davis, Wallace F. & Brajnikoff, George B.
System:
The UNT Digital Library
Empirical mode constants for calculating frequencies of axial-flow compressor blades
The vibration characteristics of a group of axial-flow compressor blades of similar geometry were investigated. Empirical-mode constants were determined for the first three bending and torsional modes. A comparison of experimentally determined frequencies of a second group of blades with frequencies computed using these mode constants showed that the computed values were correct within 10 percent. The approximate limiting ratios of depth to chord and length to chord below which these constants could not be used to compute the natural frequencies were also found experimentally.
Date:
April 23, 1948
Creator:
Millenson, M. B. & Wilterdink, P. I.
System:
The UNT Digital Library
Flight Tests to Determine the Drag of Fin-Stabilized Parabolic Bodies at Transonic and Supersonic Speeds
Report presenting testing on parabolic bodies of revolution of two fineness ratios in the transonic and supersonic range. One had a body fineness ratio of 7.87 and one had a ratio of 12 and were tested under different Mach number ranges. Experimental results and drag estimates of various portions of the body are provided.
Date:
April 21, 1948
Creator:
Alexander, Sidney R.; Chauvin, Leo T. & Rumsey, Charles B.
System:
The UNT Digital Library
Results Obtained During Accelerated Transonic Tests of the Bell XS-1 Airplane in Flights to a Mach Number of 0.92
Results are presented of tests up to a Mach number of 0.92 at altitudes around 30,000 feet. The data obtained show that the airplane can be flown to this Mach number above 30,000 feet. Longitudinal trim changes have been experienced but the forces involved have been small. The elevator effectiveness decreased about one-half with increase of Mach number from 0.70 to 0.87.
Date:
April 19, 1948
Creator:
Drake, Hubert M.; McLaughlin, Milton D. & Goodman, Harold R.
System:
The UNT Digital Library
Stability Results Obtained With Douglas D-558-1 Airplane (BuAero No. 37971) in Flight Up to a Mach Number of 0.89
Memorandum presenting measurements of some of the high-speed characteristics of the D-558-1 airplane up to Mach number 0.89. The results of the tests showed that the stabilizer incidence drastically affected the longitudinal trim characteristics above a Mach number of 0.80.
Date:
April 22, 1949
Creator:
Barlow, William H. & Lilly, Howard C.
System:
The UNT Digital Library
Analytical and experimental investigation of thrust augmentation of axial- and centrifugal-compressor turbojet engines by injection of water and alcohol in combustion chambers
Report presenting an investigation of thrust augmentation by injection of water and water-alcohol mixtures in the combustion chambers at sea-level zero-ram flight conditions on 4000-pound-thrust axial-flow and centrifugal-flow turbojet engines. Thrust augmentation, compressor characteristics, fuel flow, and turbine-outlet-temperature distributions are presented for various injection rates and water-alcohol mixtures.
Date:
April 13, 1950
Creator:
Gabriel, David S.; Dowman, Harry W. & Jones, William L.
System:
The UNT Digital Library
Evaluation of Gust and Draft Velocities From Flights of F-61C Airplanes Within Thunderstorms August 21, 1947 to August 25, 1947 at Clinton County Army Air Field, Ohio
Memorandum presenting the results of measurements of gust and draft velocities within thunderstorms at a selected air field over a 5-day period. They are also compared to previous flights.
Date:
April 2, 1948
Creator:
Funk, Jack
System:
The UNT Digital Library
General handling-qualities results obtained during acceptance flight tests of the Bell XS-1 airplane
Report presenting measurements of the handling qualities of the Bell XS-1 transonic airplane using NACA instruments. Information regarding the stability and control characteristics and aerodynamic loads was obtained using two different airplanes in gliding and powered flight. Results regarding the longitudinal and lateral stability and control and stalling characteristics are provided.
Date:
April 19, 1948
Creator:
Williams, Walter C.; Forsyth, Charles M. & Brown, Beverly P.
System:
The UNT Digital Library
Results of Preliminary Flight Tests of the XS-1 Airplane (8-Percent Wing) to a Mach Number of 1.25
Presents results of the U. S. Air Forces' accelerated transonic flight tests of the XS-1 No. 1 airplane for the Mach number range from 0.70 to 1.25 at altitudes from 30,000 to 49,000 feet. Data are included on horizontal-tail loads and buffeting, longitudinal trim changes, elevator effectiveness and control forces, and lateral trim characteristics.
Date:
April 6, 1948
Creator:
Williams, W. C. & Beeler, De E.
System:
The UNT Digital Library
Preliminary investigation of control characteristics at transonic speeds of a tapered 45 degree sweptback wing of aspect ratio 3 having a horn-balanced full-span control
Report presenting an investigation at transonic speeds in the 7- by 10-foot tunnel to determine hinge-moment and effectiveness characteristics of a horn-balanced control on an aspect-ratio-3, 45 degree sweptback wing. The investigation was extended through the transonic speed range by testing in the high velocity field over a reflection plane on the sidewall of the tunnel.
Date:
April 10, 1952
Creator:
Lowry, John G. & Fikes, Joseph E.
System:
The UNT Digital Library
Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Twisted and cambered triangular wing of aspect ratio 2 with NACA 0005-63 thickness distribution
Report presenting the results of a wind-tunnel investigation at subsonic and supersonic Mach numbers to determine the aerodynamic characteristics of a wing-body combination with a triangular wing of aspect ratio 2. The mean surface of the wing was twisted and cambered to support a nearly elliptical span load distribution at Mach number 1.53 and a lift coefficient of 0.25. Lift, drag, and pitching moment are presented for a range of Mach and Reynolds numbers.
Date:
April 10, 1952
Creator:
Heitmeyer, John C. & Petersen, Robert B.
System:
The UNT Digital Library
Experimental investigation of the drag of 30 degree, 60 degree, and 90 degree cone cylinders at Mach numbers between 1.5 and 8.2
Report presenting the total drag coefficients of 60 degree cone cylinders of fineness ratio 2.07 measured in free flight from Mach numbers of 1.5 to 8.2. Results regarding the smooth 60 degree cone cylinder, rifled models, and discontinuity lines in the shadowgraph pictures are provided.
Date:
April 25, 1952
Creator:
Seiff, Alvin & Sommer, Simon C.
System:
The UNT Digital Library
Low-speed aerodynamic characteristics of a large-scale 45 degree swept-back wing with partial-span slats, double-slotted flaps, and ailerons
Report presenting experimental data from force and pressure tests on a large-scale, semispan, wing-fuselage model. Longitudinal force and moment characteristics are given for the model with various combinations of slat spans. The wing had 45 degrees of sweepback, an aspect ratio of 6, a taper ratio of 0.5, and an NACA 64A010 section normal to the quarter-chord line of the unswept panel and had partial-span slats, aileron, and double-slotted flaps equipped.
Date:
April 28, 1952
Creator:
James, Harry A.
System:
The UNT Digital Library
Matched performance characteristics of a 16-stage axial-flow compressor and a 3-stage turbine
Report presenting component performance data for one modification of a 16-stage compressor and a 3-stage turbine to determine the matched performance characteristics of an engine with those components. The compressor surge line and infinite exhaust-nozzle-area equilibrium operating line restricted the region of matched compressor-turbine operation. Results regarding the engine operation with modified compressor and three-stage turbine, effect of leakage on engine operation, component efficiencies, and operation in the surge region are provided.
Date:
April 28, 1953
Creator:
Rebeske, John J., Jr. & Dugan, James F., Jr.
System:
The UNT Digital Library
Longitudinal Stability and Drag Characteristics at Mach Numbers From 0.75 to 1.5 of an Airplane Configuration Having a 60 Degree Swept Wing of Aspect Ratio 2.24 as Obtained From Rocket-Propelled Models
Report discussing testing of a rocket-propelled airplane configuration model and a drag model, each with a 60 degree swept wing of aspect ratio 2.24, and different fuselages, at a Mach number range of 0.75 to 1.50. Information about the longitudinal stability, control, and drag characteristics and minimum-drag characteristics is presented.
Date:
April 11, 1952
Creator:
Vitale, A. James; McFall, John C., Jr. & Morrow, John D.
System:
The UNT Digital Library
Wind-Tunnel Investigation at Low Speed of the Effects of Symmetrical Deflection of Half-Delta Tip Controls on the Damping in Roll and Yawing Moment Due to Rolling of a Triangular-Wing Model
Report presenting a low-speed investigation in the stability tunnel to determine the effects of symmetrical deflection of half-delta tip controls on the damping in roll and yawing moment due to rolling of a model with triangular wings. Triangular wings have numerous aerodynamic advantages, but it is difficult to obtain adequate longitudinal and lateral control with acceptable control forces when using them. Results regarding the lift characteristics and rolling characteristics are provided.
Date:
April 6, 1951
Creator:
Wolhart, Walter D.
System:
The UNT Digital Library