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Wind-tunnel tests of spoilers on tail surfaces
Report presenting wind-tunnel testing in two-dimensional and three-dimensional flow to investigate the aerodynamic characteristics of spoilers on tail surfaces for low-speed flight. Test results indicated that spoilers on tail surfaces showed little possibility of replacing conventional control surfaces. Results regarding a flap alone, rear spoiler alone, forward spoiler alone, forward spoiler and flap, and a combination of forward and rear spoilers on upper and lower surfaces in both types of flow are provided.
Date:
August 1945
Creator:
Liddell, Robert B.
System:
The UNT Digital Library
Tests of a Linked Differential Flap System Designed to Minimize the Reduction in Effective Dihedral Caused by Power
Report discusses the results of testing on a linked differential flap system upon the effective-dihedral characteristics of an airplane scale model. The negative dihedral changes caused by power can be materially reduced or eliminated by use of a differential flap system. The static directional stability also increased with differential flap action.
Date:
August 1945
Creator:
Pitkin, Marvin & Schade, Robert O.
System:
The UNT Digital Library
Investigation of some wake vortex characteristics of an inclined ogive-cylinder body at Mach number 1.98
Report presenting measurements of the pitot-pressure distributions in the flow field, pressure distributions over the body, and downwash distributions through shed vortices for an inclined body of revolution at a free-stream Mach number of 1.98. Results regarding the experimental pressure distributions and vortex positions, vortex strengths computed from experiment, comparisons of theoretical and experimental vortex paths, and comparisons of theoretical and experimental downwash distributions through the body vortices are provided.
Date:
August 23, 1955
Creator:
Jorgensen, Leland H. & Perkins, Edward W.
System:
The UNT Digital Library
Investigation of Equilibrium Temperatures and Average Laminar Heat-Transfer Coefficients for the Front Half of Swept Circular Cylinders at a Mach Number of 6.9
Report presenting the average heat-transfer coefficients and equilibrium temperatures for the front half of an isothermal cylinder with a laminar boundary layer as determined by wind tunnel testing at Mach number 6.9 and a range of Reynolds numbers and sweep angles.
Date:
August 18, 1955
Creator:
Feller, William V.
System:
The UNT Digital Library
Preliminary performance data of several tail-pipe-cascade-type model thrust reversers
Report presenting the reverse-thrust performance of several tail-pipe-cascade-type model thrust reversers over a range of exhaust-nozzle pressure ratios from 1.2 to 2.4. Both symmetrical and asymmetrical cascade blade shapes were investigated. Results regarding the performance of tail-pipe-cascade-type model thrust reversers having symmetrically shaped cascade blades and the performance of tail-pipe-cascade-type model thrust reversers having asymmetrically shaped cascade blades are provided.
Date:
August 29, 1955
Creator:
Henzel, James G., Jr. & McArdle, Jack G.
System:
The UNT Digital Library
Theoretical Investigation of Laminar Heat Transfer on Yawed Infinite Cylinders in Supersonic Flow and a Comparison With Experimental Data
Report presenting a theoretical method for calculating heat transfer in the laminar boundary layer on yawed infinite cylinders in compressible flow. The method can be applied to a cylinder of arbitrary cross section and arbitrary chordwise wall-temperature distribution. The variation in local heat transfer around the surface of the cylinder was found to have little functional dependence on yaw angle or wall temperature.
Date:
August 9, 1955
Creator:
Beckwith, Ivan E.
System:
The UNT Digital Library
Experimental investigation of a transonic compressor rotor with a 1.5-inch chord length and an aspect ratio of 3.0 2: blade-element performance
Report presenting a transonic compressor rotor with double-circular-arc blade sections, which were designed and tested to investigate the aerodynamic effects of using a short blade chord and a high aspect ratio. The report presents the blade-element performance and performance analysis.
Date:
August 18, 1955
Creator:
Schwenk, Francis C. & Tysl, Edward R.
System:
The UNT Digital Library
Hinge Moments of Sealed-Internal-Balance Arrangements for Control Surfaces 2: Experimental Investigation of Fabric Seals in the Presence of a Thin-Plate Overhang
Report presenting tests in a seal test chamber to determine the hinge moments contributed by the fabric seal in an internal-balance arrangement employing a thin-plate overhang. The tests were performed with various widths of fabric sealing various widths of flap-nose gap, with a horizontal, a vertical, and a circular type of wing structure forward of the balance, and with various heights of balance chamber. Results regarding seal-profile photographs, desired seal-moment characteristics, experimental seal-moment characteristics, effect of the balance configuration on the seal-moment characteristics, comparison of analytical and experimental seal-moment characteristics, computation of seal-moment characteristics by the approximate method, and application of the data are provided.
Date:
August 1945
Creator:
Fischel, Jack
System:
The UNT Digital Library
Hinge Moments of Sealed-Internal-Balance Arrangements for Control Surfaces 1: Theoretical Investigation
Report presenting the results of a theoretical analysis of the hinge-moment characteristics of various sealed-internal-balance arrangements for control surfaces. The results of the investigation indicated that the most nearly linear control-surface hinge-moment characteristics can probably be obtained from a flexible seal over a narrow gap, which is so installed that the motion of the seal is restricted to a region behind the point of attachment of the seal to the wing structure.
Date:
August 1945
Creator:
Murray, Harry E. & Erwin, Mary A.
System:
The UNT Digital Library
Tests of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2: Two Aluminum-Alloy Models of 20-Inch Chord With 0.064- and 0.081-Inch-Thick Skin
Report presenting testing of two 2024-T3 aluminum-alloy multiweb wing structures (MW-2 and MW-3), similar to airplane or missile wings, at a Mach number of 2 under simulated supersonic flight conditions. Results regarding experimentally determined test conditions, model temperatures, strain-gage results, and model failures are provided. The report indicates that much of the stress data does not agree with expected results, but there is too much uncertainty regarding the reduction of strain data that no conclusions can be made concerning the results.
Date:
August 9, 1955
Creator:
Griffith, George E.; Miltonberger, Georgene H. & Rosecrans, Richard
System:
The UNT Digital Library
A preliminary investigation of static-pressure changes associated with combustion of aluminum borohydride in a supersonic wind tunnel
Report presenting static-pressure changes resulting from steady combustion of aluminum borohydride in a supersonic wind tunnel. Static pressures were measured along the top wall of a tunnel adjacent to the flame that filled the upper portion of the test section. Results regarding the static-pressure increases, effect of change in fuel-injection rate, and effect of tunnel boundary layer on the character of the heat-addition region are provided.
Date:
August 18, 1955
Creator:
Dorsch, Robert G.; Serafini, John S. & Fletcher, Edward A.
System:
The UNT Digital Library
Performance of Inconel 550 Turbine Blades in a Turbojet Engine and Effects of Different Forging Temperatures and Heat Treatments
Report presenting an investigation to determine the effects of forging at 1950 degrees and 2150 degrees Fahrenheit as well as the effects of several heat treatments on the performance of Inconel 550 in a turbojet engine. Differences in engine performance of the different turbine blades could not be associated with consistent differences in microstructure or grain size. Results regarding blade performance, blade elongation during engine operation, microstructure of as-heat-treated blades, grain size, metallurgical studies of failed blades, stress-rupture tests, and hardness are provided.
Date:
August 16, 1955
Creator:
Gyorgak, C. A.; Johnston, J. R. & Weeton, J. W.
System:
The UNT Digital Library
Analysis of Vertical-Tail Loads in Rolling Pull-Out Maneuvers
Bulletin presenting an analysis of the vertical-tail loads to be expected as a result of abrupt aileron action in accelerated flight, as in rolls from turns or pull-outs, for example. Critical tail loads may occur in rolling pull-out maneuvers, particularly on airplanes with good ailerons and low directional stability.
Date:
August 1944
Creator:
Gilruth, Robert R.
System:
The UNT Digital Library
Flight Measurements of the Lateral Response Characteristics of the Convair XF-92A Delta-Wing Airplane
Memorandum presenting rudder pulse maneuvers obtained with the Convair XF-92A delta-wing research airplane at an altitude of about 30,000 feet over a Mach number range of 0.52 to 0.92. Tests were made with and without a wing fence. By analyzing the maneuvers, the characteristics of the airplane transient, airplane stability derivatives, and frequency-response characteristics were measured.
Date:
August 5, 1955
Creator:
Holleman, Euclid C.
System:
The UNT Digital Library
Performance of a short combustor at high altitudes using hydrogen fuel
Performance characteristics of a 16-inch annular-type combustor installed in a full-scale engine using gaseous-hydrogen fuel were obtained at simulated altitudes from 66,000 to 86,000 feet at a flight Mach number of 0.8. Combustion efficiencies of 86 percent were obtained at 86,000 feet (combustor pressure, 420 lb/sq ft abs). Combustor blowout was not encountered during the investigation.
Date:
August 7, 1956
Creator:
Sivo, Joseph N. & Fenn, David B.
System:
The UNT Digital Library
Preliminary Vibration and Flutter Studies on P-47 Tail
Report presenting a report illustrated by photographs and vibration records on the failure of the P-47 rudder in the high-speed tunnel at a true speed of 468 miles per hour and a density corresponding to 9000 feet altitude. The fin-rudder unit was tested as being at least representative of the tail design of the P-47 airplane.
Date:
August 1943
Creator:
Theodorsen, Theodore
System:
The UNT Digital Library
Wind Tunnel Tests of Ailerons at Various Speeds 4: Ailerons of 0.20 Airfoil Chord and True Contour With 0.35 Aileron-Chord Extreme Blunt-Nose Balance on the NACA 23012 Airfoil
Report presenting tests made on an NACA 23012 airfoil fitted with a 20-percent-chord, true-contour aileron with 35-percent-chord, extreme blunt-nose balance. The primary purpose of the investigation was to determine the variation of the aerodynamic characteristics of this type of aileron with airspeed; the effect of variations of gap width and balance-nose radii was also investigated. Results regarding hinge moments, lift, and pitching-moment coefficients are provided.
Date:
August 1943
Creator:
Anderson, R. A.
System:
The UNT Digital Library
Aircraft-Fuel-Tank Design for Liquid Hydrogen
"Some of the considerations involved in the design of aircraft fuel tanks for liquid hydrogen are discussed herein. Several of the physical properties of metals and thermal insulators in the temperature range from ambient to liquid-hydrogen temperatures are assembled. Calculations based on these properties indicate that it is possible to build a large-size liquid-hydrogen fuel tank which (1) will weigh less then 15 percent of the fuel weight, (2) will have a hydrogen vaporization rate less than 30 percent of the cruise fuel-flow rate, and (3) can be held in a stand-by condition and readied for flight in a short time" (p. 1).
Date:
August 9, 1955
Creator:
Reynolds, T. W.
System:
The UNT Digital Library
Experimental investigation of methods of improving diffuser-exit total-pressure profiles for side-inlet model at Mach number 3.05
Report presenting an investigation of several methods of straightening diffuser-exit total-pressure profiles produced by a typical half-conical double-shock side inlet at a free stream Mach number of 3.05. The methods included the use of longer subsonic diffusers, constant-area mixing sections at the diffuser exit, internal screens, a rapid acceleration of the flow at the diffuser exit, internal bleed, and a change in internal-flow passage shape obtained by raising the internal centerbody fairing from the floor into the diffuser duct. Each of the methods was found to be effective in reducing distortion.
Date:
August 29, 1955
Creator:
Piercy, Thomas G. & Klann, John L.
System:
The UNT Digital Library
Drag Near Zero Lift of a 1/7-Scale Model of the Convair B-58 External Store as Measured in Free Flight Between Mach Numbers of 0.8 and 2.45
"The zero-lift drag of a 1/7-scale model of the Convair B-58 external store was obtained at mach numbers between 0.8 and 2.45 at corresponding Reynolds numbers per foot of 3.5 x 10 to the 6th power and 15.3 X 10 to the 6th power. The experimental drag data are compared with calculated values at both subsonic and supersonic speeds and show good agreement. In addition to the drag data, some static stability derivatives and damping factors were also obtained and are presented with the predicted values of these derivatives for completeness and for comparison" (p. 1).
Date:
August 3, 1955
Creator:
Hopko, Russell N.
System:
The UNT Digital Library
An investigation of aircraft heaters 13: performance of corrugated and noncorrugated fluted type exhaust gas-air heat exchangers
Report presenting thermal and static pressure-drop performance data on three fluted-type heat exchangers. Two of the heaters used corrugated surfaces along the fluid passages and the third one was constructed with non-corrugated surfaces. Results regarding a comparison of results on the noncorrugated heater using two different air shrouds, heat transfer, isothermal static pressure drop, nonisothermal static pressure drop, and heater surface temperatures are provided.
Date:
August 1943
Creator:
Boelter, L. M. K.; Guibert, A. G.; Miller, M. A. & Morrin, E. H.
System:
The UNT Digital Library
An Investigation of Aircraft Heaters 14: Performance of Two Finned-Type Crossflow Exhaust Gas and Air Heat Exchangers
Report presenting data on the thermal performance and the static pressure drop characteristics of two finned-type exhaust gas and air heat exchangers. One heater was constructed of copper and stainless steel while the other was constructed from aluminum alloy. The measured thermal outputs and static pressure drops are compared with predicted magnitudes.
Date:
August 1944
Creator:
Boelter, L. M. K.; Guibert, A. G.; Rademacher, J. M. & Sloggy, L. J. B.
System:
The UNT Digital Library
High-speed drag tests of several fuselage shapes in combination with a wing
Drag testing was conducted in the high-speed wind tunnel of 23 conditions combining six streamline shapes and three conventional cowling-fuselage bodies. All of the models were tested in combination with a wing in order to include wing-fuselage interference effects. The critical speeds of combinations tested were, in general, determined by the wing-fuselage juncture.
Date:
August 1940
Creator:
Draley, Eugene C.
System:
The UNT Digital Library
Investigation of impulse-type supersonic compressor with hub-tip ratio of 0.6 and turning to axial direction 2: stage performance with three different sets of stators
Report presenting an impulse-type supersonic compressor designed for turning to the axial direction that was tested in air with three different sets of stator blades at eight angle settings.
Date:
August 16, 1955
Creator:
Wilcox, Ward W.
System:
The UNT Digital Library