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Effects of boundary-layer control on the longitudinal characteristics of a 45 degrees swept-forward wing-fuselage combination
Report presenting an investigation to determine the benefits obtainable by applying boundary-layer control to a 45 degree swept-forward wing-fuselage combination. Force and pressure-distribution data were obtained with and without boundary-layer control with various combinations of leading-edge and trailing-edge flaps.
Date:
February 2, 1950
Creator:
McCormack, Gerald M. & Cook, Woodrow L.
System:
The UNT Digital Library
Wing-tunnel investigation at Mach numbers from 0.50 to 1.29 of an all-movable triangular wing of aspect ratio 4 alone and with a body
Report presenting the aerodynamic characteristics of an all-movable, triangular-plan-form wing alone and with a body as determined from semispan model tests. The agreement between calculated and experimental results was not satisfactory for the most part, which seemed to be due to the failure of linear theory to define the actual flow field about the configurations investigated. Results regarding lift characteristics, drag characteristics, and pitching-moment characteristics are provided.
Date:
February 2, 1950
Creator:
Stivers, Louis S. & Malick, Alexander W.
System:
The UNT Digital Library
Correlation of laboratory smoke test with carbon deposition in turbojet combustors
Report presenting a correlation of carbon deposition of 19 fuels in a turbojet combustor as a function of the boiling point and of the flame height at the sooting point of the fuels in a simple wick lamp for a particular combustor operating at a single set of conditions. Two similar investigations with different combustors, operating conditions, and nine different fuels yielded similar correlations on the same graph.
Date:
February 3, 1950
Creator:
Busch, Arthur M.
System:
The UNT Digital Library
The effect of aspect ratio on the subsonic aerodynamic characteristics of wings with NACA 65(sub 1)-210 sections
Report presenting the results of tests of four model wings of aspect ratios 1, 2, 4, and 6 and with NACA 65(sub 1)-210 sections. The experimental lift-curve slope is compared with predictions from theory. Results regarding lift, drag, and pitching moment, lift-curve slope, drag divergence, minimum drag, and pitching moment are provided.
Date:
February 3, 1950
Creator:
Nelson, Warren H. & Erickson, Albert L.
System:
The UNT Digital Library
Investigation of the NACA 4-(4)(06)-057-45a and NACA 4-(4)(06)-57-45b Two-Blade Swept Propellers at Forward Mach Numbers to 0.925
Report presenting an investigation of the NACA 4-(4)(06)-057-45A and NACA 4-(4)(06)-057-45B two-blade swept propellers in the high-speed tunnel at blade angles of 25 degrees, 55 degrees, 60 degrees, 65 degrees, and 70 degrees. The swept propellers were compared with straight propellers and were found to be 10 percent more efficient at a forward Mach number of 0.85 for the design blade angle of 60 degrees. Results regarding the effect of forward Mach number, blade sweep, advance ratio, and constant power coefficient on efficiency are also provided.
Date:
February 6, 1950
Creator:
Delano, James B. & Harrison, Daniel E.
System:
The UNT Digital Library
Longitudinal Trim and Drag Characteristics of Rocket-Propelled Models Representing Two Airplane Configurations
Report discussing an investigation of the longitudinal trim and drag characteristics of two airplane configurations through the transonic speed range. One configuration had a thin straight wing and tail and one had a thicker 35 degree sweptback wing and a 46 degree sweptback tail on the same fuselage-fin arrangement. Information about the control effectiveness and stability and application to a full-scale airplane is also provided.
Date:
February 6, 1950
Creator:
Parks, James H. & Mitchell, Jesse L.
System:
The UNT Digital Library
Temperature survey of the wake of two closely located parallel jets
Report presenting a temperature survey made in the wake of two closely located parallel jets emerging into the atmosphere from two types of twin convergent nozzles. Results regarding the twin unshrouded nozzles and twin nozzles with twin geometry-simulated shrouds are provided.
Date:
February 6, 1950
Creator:
Sloop, John L. & Morrell, Gerald
System:
The UNT Digital Library
Lateral-Control Investigation at a Reynolds Number of 5,300,000 of a Wing of Aspect Ratio 5.8 Sweptforward 32 Degrees at the Leading Edge
Memorandum presenting the low-speed lateral control characteristics of a 32 degree sweptforward wing of aspect ratio 5.8 and NACA 65-series airfoil sections as determined in the 19-foot pressure tunnel. The investigation include the measurement of the hinge-moment and normal-force characteristics of an aileron and the rolling-effectiveness characteristics of the aileron and several configurations of spoilers.
Date:
February 7, 1950
Creator:
Graham, Robert R.
System:
The UNT Digital Library
Aerodynamic Investigation of a Parabolic Body of Revolution at Mach Number of 1.92 and Some Effects of an Annular Jet Exhausting From the Base
Report discussing an investigation of a parabolic body of revolution with and without the effects of an annular jet exhausting from the base. The aerodynamic characteristics, pressures, lift-curve slope, and other characteristics with the jet in operation and inoperative were compared.
Date:
February 8, 1950
Creator:
Love, Eugene S.
System:
The UNT Digital Library
Altitude-wind-tunnel investigation of tail-pipe burner with converging conical burner section on J35-A-5 turbojet engine
An investigation of turbojet-engine thrust augmentation by means of tail-pipe burning has been conducted in the NACA Lewis altitude wind tunnel.
Date:
February 10, 1950
Creator:
Thorman, H. Carl & Campbell, Carl E.
System:
The UNT Digital Library
Planing Characteristics of Six Surfaces Representative of Hydro-Ski Forms
Report presenting the planing characteristics for six surfaces representative of hydro-ski forms as determined by tank tests.Testing was made at specified trims, speeds, and sufficient loads to define variations with wetted length. Data from the testing is provided in the form of plots of wetted length, load, resistance, trimming moment, and draft against wetted area.
Date:
February 10, 1950
Creator:
Wadlin, Kenneth L. & McGehee, John R.
System:
The UNT Digital Library
Analytical Investigation of Propeller Efficiency at High Subsonic Flight Speeds near Mach Number Unity
From Introduction: "Tests have recently been conducted in the Langley 8-foot high-speed tunnel (reference 1) to study the effects of changes in operating advance ratio, blade plan form, blade-section thickness, section camber, and other variables on the on the propeller characteristics in the transonic-speed range. The method in reference 2, which evaluated the profile drag losses and the induced losses seperately, is followed in this paper. The method as presented offers the general prediction of propeller performance, and can be used to supplement the experimental data."
Date:
February 13, 1950
Creator:
Gilman, Jean, Jr.; Crigler, John L. & McLean, F. Edward
System:
The UNT Digital Library
Effects of Obstructions in Compressor Inlet on Blade Vibration in 10-Stage Axial-Flow Compressor
Report presenting a blade-vibration survey that was conducted during normal operation of a 10-stage axial-flow compressor powered by part of a complete jet engine. Strain-gage records were obtained from all stages during acceleration, deceleration, and constant-speed runs. Results regarding the inlet disturbances and damping characteristics are provided.
Date:
February 13, 1950
Creator:
Meyer, André J., Jr.; Calvert, Howard F. & Morse, C. Robert
System:
The UNT Digital Library
The Time Lag Between Flap Deflection and Force Development at a Mach Number of 4
Report presenting an investigation of the time lag between flap deflection and force development on a rectangular wing with a 9-percent-thick symmetrical circular-arc profile with a full-span 30-percent-chord flap. This was performed in order to determine further information about the rapidity of response for a supersonic missile after a given flap deflection due to the potential time lag between the deflection of the controls surfaces and the development of aerodynamic forces.
Date:
February 13, 1950
Creator:
Lindsey, Walter F. & Ulmann, Edward F.
System:
The UNT Digital Library
Maximum-Lift Investigation at Mach Numbers From 0.05 to 1.20 of a Wing With Leading Edge Swept Back 42 Degrees
Report presenting an investigation at subsonic and transonic speeds to determine the aerodynamic characteristics of three geometrically similar wings with 42 degree sweepback of the leading edge, aspect ratio 4, taper ratio 0.625, and NACA 64(sub)1-112 airfoils. The lift, drag, and pitching-moment characteristics are provided.
Date:
February 14, 1950
Creator:
Turner, Thomas R.
System:
The UNT Digital Library
Pressure Distributions on the Blade Sections of the NACA 10-(3)(049)-033 Propeller Under Operating Conditions
A report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for nine radial stations of the NACA 10-(3)(049)-033 propeller.
Date:
February 14, 1950
Creator:
Gray, W. H. & Hunt, Robert M.
System:
The UNT Digital Library
Spin-Tunnel Investigation of a Model of a 60 Degree Delta-Wing Airplane to Determine the Spin, Recovery, and Longitudinal Trim Characteristics Throughout an Extensive Range of Mass Loadings
Report presenting an investigation to determine the spin, recovery, and longitudinal-trim characteristics of a 60 degree delta-wing model through an extensive range of mass loadings. Variations in the relative density, center-of-gravity position, and inertia parameters were included in testing. Results regarding the single-vertical-tail and multiple-vertical-tail configurations are provided.
Date:
February 15, 1950
Creator:
Klinar, Walter J. & Jones, Ira P., Jr.
System:
The UNT Digital Library
Temperature and pressure distributions in dual parallel jets impinging on the ground from a turbojet engine
Report presenting an investigation to determine the temperature and pressure distributions in the jets issuing from two parallel nozzles of a turbojet engine located close together and impinging on the ground at an angle of 20 degrees. Results regarding the jet-nozzle pressure ratio, constant-temperature parameters, and temperature contours are provided.
Date:
February 20, 1950
Creator:
Farmer, J. Elmo; Stepka, Francis S. & Garrett, Floyd B.
System:
The UNT Digital Library
Free-Flight Investigation of the Static and Dynamic Longitudinal Stability Characteristics of 1/3.7-Scale Rocket-Powered Models of the Bell MX-776A
"An investigation of the static and dynamic longitudinal stability characteristics of 1/3.7 scale rocket-powered model of the Bell MX-776A has been made for a Mach number range from 0.8 to 1.6. Two models were tested with all control surfaces at 0 degree deflection and centers of gravity located 1/4 and 1/2 body diameters, respectively, ahead of the equivalent design location. Both models were stable about the trim conditions but did not trim at 0 degree angle of attack because of slight constructional asymmetries" (p. 1).
Date:
February 21, 1950
Creator:
Michal, David H.
System:
The UNT Digital Library
An 8-Foot Axisymmetrical Fixed Nozzle for Subsonic Mach Numbers Up to 0.99 and for a Supersonic Mach Number of 1.2
From Introduction: "This paper, which should be of interest to those concerned with transonic wind tunnels, covers the design and operating characteristics of the nozzle."
Date:
February 23, 1950
Creator:
Ritchie, Virgil S.; Wright, Ray H. & Tulin, Marshall P.
System:
The UNT Digital Library
Investigation of downwash and wake characteristics at a Mach number of 1.53 3: swept wings
Report presenting the results of an experimental investigation of the downwash and wake characteristics behind two highly swept wings in a supersonic stream. Results regarding the rate of change of downwash with angle of attack at zero lift, variation of downwash angle with angle of attack, and wake are provided.
Date:
February 23, 1950
Creator:
Perkins, Edward W. & Canning, Thomas N.
System:
The UNT Digital Library
Tests of a small-scale NACA submerged inlet at transonic Mach numbers
Report presenting the pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspect ratio 5 measured in the Mach number range of 0.60 to 1.08 by the wing-flow method. Variation of ram-recovery ratio determined from measurements at the center line of the inlet with test station Mach number is presented for mass-flow ratios of 0.30 to 0.60. Results regarding the pressure-recovery characteristics and application of the data to fuselage installations are provided.
Date:
February 23, 1950
Creator:
Rolls, L. Stewart & Rathert, George A., Jr.
System:
The UNT Digital Library
Aerodynamic characteristics of a wing with quarter-chord line swept back 60 degrees, aspect ratio 2, taper ratio 0.6, and NACA 65A006 airfoil section : transonic bump method
From Introduction: "This paper presents the results of the investigation of the wing-alone and wing-fuselage configurations employing a wing with the quarter-chord line swept back 60^o, aspect ratio 2, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the free stream."
Date:
February 24, 1950
Creator:
Myers, Boyd C., II & King, Thomas J., Jr.
System:
The UNT Digital Library
Determination of Minimum Moments of Inertia of Arbitrarily Shaped Areas, Such as Hollow Turbine Blades
Memorandum presenting a method for approximately determining the minimum moment of inertia of an arbitrarily shaped area, such as the section of a hollow turbine blade. The practical application of the method involves a simple routine tabular procedure.
Date:
February 24, 1950
Creator:
Gendler, Sel & Johnson, Donald F.
System:
The UNT Digital Library