Technical Report Archive & Image Library (TRAIL) - 5,157 Matching Results

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High-Speed Cascade Tests of a Blade Section Designed for Typical Hub Conditions of High-Flow Transonic Rotors

Description: Report discussing high-speed cascade tests made of a blade section designed for conditions typical of the hub section of high-flow transonic rotors. The intent of the testing is to provide information on the effects of local surface Mach numbers on blade performance. The test results, effect of more forward location on peak surface velocities, effect of increase in pressure-rise coefficient, effect of Mach number and pressure rise on turning angle, and a comparison of variation in momentum-loss… more
Date: September 28, 1955
Creator: Savage, Melvyn; Felix, A. Richard & Emery, James C.
Partner: UNT Libraries Government Documents Department
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Performance of Inconel 550 Turbine Blades in a Turbojet Engine and Effects of Different Forging Temperatures and Heat Treatments

Description: 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 … more
Date: August 16, 1955
Creator: Gyorgak, C. A.; Johnston, J. R. & Weeton, J. W.
Partner: UNT Libraries Government Documents Department
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Lateral Stability and Control Measurements of a Fighter-Type Airplane With a Low-Aspect-Ratio Unswept Wing and a Tee-Tail

Description: Report presenting an investigation of the lateral stability and control effectiveness of a model of a fighter-type airplane model with a low-aspect-ratio and 3.4-percent-thick wing with negative dihedral at a range of Mach numbers, sideslip angles, and angles of attack. Results regarding the lateral characteristics at zero angle of attack, lifting conditions, and lateral and directional controls are provided.
Date: June 12, 1956
Creator: Arabian, Donald D. & Schmeer, James W.
Partner: UNT Libraries Government Documents Department
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Drag and rolling-moment effectiveness of trailing-edge spoilers at Mach numbers 2.2 and 5.0

Description: Report presenting free-flight measurements of the rolling effectiveness and drag of trailing-edge spoilers on low-aspect-ratio wings with both laminar and turbulent boundary layers at two different Mach numbers. The effect of a spoiler deflected from the surface of a wing is to cause boundary-layer separation upstream.
Date: October 3, 1955
Creator: Canning, Thomas N. & DeRose, Charles E.
Partner: UNT Libraries Government Documents Department
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Flight Measurements of the Lateral Response Characteristics of the Convair XF-92A Delta-Wing Airplane

Description: 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.
Partner: UNT Libraries Government Documents Department
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Distribution of losses behind a compressor rotor as measured by a rotating rake

Description: Report presenting a rotating total-pressure survey rake to obtain wake measurements of a compressor rotor. Results indicated that there was a considerable radial flow of the inboard-blade boundary layer and little radial flow of the inner casing boundary layer. Results regarding the variation in total-pressure-loss distribution with Mach number, variation in total-pressure-loss distribution with angle of attack, contour plots, spanwise variation in total-pressure-loss coefficient, variation of … more
Date: January 17, 1956
Creator: Godwin, William R.
Partner: UNT Libraries Government Documents Department
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Investigation of a high-pressure-ratio eight-stage axial-flow research compressor with two transonic inlet stages 6: over-all performance, rotating stall, and blade vibration at low and intermediate compressor speeds

Description: Report presenting an investigation to determine the overall performance of the modified eight-stage axial-flow compressor with new fourth-stage stator blades as part of a study of the problems encountered in a high-pressure-ratio axial-flow compressor with transonic inlet stages. The performance of the compressor was determined over a range of weight flows at equivalent speeds from 30 to 100 percent of design speed.
Date: November 1, 1955
Creator: Standahar, Raymond M.; Hanson, Morgan P. & Geye, Richard P.
Partner: UNT Libraries Government Documents Department
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Longitudinal Characteristics at Transonic and Supersonic Speeds of a Rocket-Propelled Airplane Model Having a 60-Degree Delta Wing and Low Swept Horizontal Tail

Description: Report presenting measurements of the longitudinal stability, lift, and drag characteristics of an airplane configuration with a 60 degree delta wing and a swept horizontal tail mounted near the wing plane extended at a range of Mach numbers using the rocket-model technique. Comparisons are made to data form a similar model with the tail mounted above the wing plane.
Date: September 15, 1955
Creator: Peck, Robert F. & Coltrane, Lucille C.
Partner: UNT Libraries Government Documents Department
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Transonic wind-tunnel investigation of the effects of external stores and store position on the aerodynamic characteristics of a 1/16-scale model of the Douglas D-558-II research airplane

Description: Report presenting an investigation in the transonic tunnel to determine the effects of adding external, pylon-suspended stores to a model of the Douglas D-558-II research airplane. Tests were made for two spanwise store locations and covered a range of angles of attack and Mach numbers. Results regarding the drag, lift, and pitching-moment characteristics are provided.
Date: November 8, 1955
Creator: Kelly, Thomas C.
Partner: UNT Libraries Government Documents Department
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Free-flight investigation to obtain drag-at-lift and stability data for a 60 degree delta-wing-body configuration over a Mach number range of 1.3 to 1.6

Description: Report presenting flight tests using a rocket-propelled 60 degree delta-wing body configuration, which included a NACA 0003-63 wing airfoil section. Drag at lift and stability data were obtained for a range of Mach numbers.
Date: October 6, 1955
Creator: Welsh, Clement J.
Partner: UNT Libraries Government Documents Department
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Flight measurements of directional stability to a Mach number of 1.48 for an airplane tested with three different vertical tail configurations

Description: Report presenting flight tests to measure the directional stability of a fighter-type airplane over a range of Mach numbers. Testing occurred at two altitudes and used three vertical tails of varying aspect ratio or area.
Date: October 7, 1955
Creator: Drake, Hubert M.; Finch, Thomas W. & Peele, James R.
Partner: UNT Libraries Government Documents Department
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Effect of inlet-air-flow-distortions on steady-state performance of J65-B-3 turbojet engine

Description: The effects of inlet-air-flow distortions on the performance of the J65-B-3 turbojet engine were determined over a range of altitudes from 15,000 to 50,000 feet at a flight Mach number of 0.8. Radial inlet-air-flow distortions apparently do not affect the radial distribution of pressure after the first few compressor stages, while the circumferential inlet-air-flow distortion carried completely through the engine. For the distortions investigated, at rated exhaust-gas temperature and fixed-area… more
Date: January 25, 1956
Creator: Smith, Ivan D.; Braithwaite, W. M. & Calvert, Howard F.
Partner: UNT Libraries Government Documents Department
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The effect of inlet installation on the zero-lift drag of a 60 degree delta-wing-body configuration from flight tests at Mach numbers from 0.8 to 1.86

Description: Report presenting zero-lift drag results for two 60 degree delta-wing configurations with air inlets. One had twin conical-shock semi-circular scoops just ahead of the wing-body juncture and one had a modified wing section over the inboard portion to allow installation of modified triangular inlets in the wing leading edge. Results regarding the drag coefficients and mass-flow ratios are provided.
Date: December 15, 1955
Creator: Merlet, Charles F.
Partner: UNT Libraries Government Documents Department
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Longitudinal Aerodynamic Characteristics at Transonic Speeds of a Complete Model With an Unswept Wing and a Sweptback Horizontal Tail at Two Vertical Locations

Description: Memorandum presenting an investigation to determine the static longitudinal stability contribution of a horizontal tail at two vertical locations behind a 4-percent-thick unswept-wing-fuselage combination at transonic speeds. The model used in tests is comprised of an unswept wing located in the midwing position on a body of revolution and a sweptback horizontal tail mounted on a vertical tail.
Date: September 1, 1955
Creator: Hieser, Gerald & Kudlacik, Louis
Partner: UNT Libraries Government Documents Department
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Some design implications of the effects of aerodynamic heating

Description: Report presenting an examination of creep and thermal buckling in order to determine their effect on the design of structures for high-speed aircraft. Consideration is given to the use of insulation as a means of alleviating the effect of aerodynamic heating. Creep did not appear to be a significant factor, but thermal buckling may have a substantial effect on the structural design.
Date: July 28, 1955
Creator: Heldenfels, Richard R.
Partner: UNT Libraries Government Documents Department
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Analysis of Low-Temperature Nuclear-Powered Ram-Jet Missile for High Altitudes

Description: Report presenting the gross weight and uranium investment of nuclear-powered, direct-air, shieldless, ram-jet missiles for a range of altitudes and Mach numbers. Results regarding the effect of reactor operating conditions and flight conditions on ramjet performance and effect of assumptions on ramjet performance are provided.
Date: November 9, 1955
Creator: Sams, Eldon W. & Rom, Frank E.
Partner: UNT Libraries Government Documents Department
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A variable-geometry axisymmetric supersonic inlet with telescoping centerbody

Description: Report presenting an examination of the use of an axisymmetric variable-geometry technique for achieving good supersonic inlet performance over a wide range of Mach numbers. An inlet with a telescoping spike was designed and experimentally evaluated. Results regarding the spike survey study and variable-geometry-inlet study are provided.
Date: September 7, 1955
Creator: Connors, James F. & Meyer, Rudolph C.
Partner: UNT Libraries Government Documents Department
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Performance of a short combustor at high altitudes using hydrogen fuel

Description: 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.
Partner: UNT Libraries Government Documents Department
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Some Effects of Sweep and Aspect Ratio on the Transonic Flutter Characteristics of a Series of Thin Cantilever Wings Having a Taper Ratio of 0.6

Description: Report presenting an investigation of the flutter characteristics of a series of thin cantilever wings with taper ratios of 0.6 for a range of Mach numbers. Results regarding flutter frequencies, time histories, effects of sweep on the flutter-speed ratio, effects of aspect ratio on the flutter-speed ratio, effects of additional models on the reference flutter speed, application of the flutter-speed ratio, and modified experimental flutter-speed coefficient are provided.
Date: January 24, 1956
Creator: Unangst, John R. & Jones, George W., Jr.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of the Static Longitudinal and Lateral Stability of the Bell X-1A at Supersonic Speeds

Description: "An investigation to determine the static longitudinal and lateral stability characteristics of a 1/62-scale model of the Bell X-1A has been conducted in the Langley 9-inch supersonic tunnel. tests were made at Mach numbers of 1.62, 1.94, 2.22, 2.40, and 2.62 on the wing-body, wing-body-vertical-tail, and complete configurations. Data are presented for both the body and stability axes. Detailed analysis of the test results is omitted" (p. 1).
Date: October 27, 1955
Creator: Henderson, Arthur, Jr.
Partner: UNT Libraries Government Documents Department
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Lift, drag, and longitudinal stability at Mach numbers from 1.4 to 2.3 of a rocket-powered model having a 52.5 degree sweptback wing of aspect ratio 3 and inline tail surfaces

Description: Report presenting an investigation of a configuration with a body of fineness ratio 16.9, a 52.5 degree sweptback wing of aspect ratio 3, taper ratio 0.2, and NACA 65A004 airfoil section, and an incline tail which was aeropulsed continuously in pitching during free flight with and without a sustainer rocket motor operating. The Mach number range covered was from 1.4 to 2.3. Results regarding drag, total normal force and pitching moment, wing normal-force-curve slope, flow conditions at the hori… more
Date: December 15, 1955
Creator: Gillespie, Warren, Jr.
Partner: UNT Libraries Government Documents Department
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Interaction of a Jet and Flat Plate Located in an Airstream

Description: Report presenting an evaluation of the interaction between a flat plate and a nearby jet issuing from a convergent nozzle over a range of pressure ratios and free-stream Mach numbers. The effect on the interaction of the presence of streamline, blunt-base, and curved-base fairings between the plate and parabolic afterbody housing the exit nozzle was also investigated.
Date: September 8, 1955
Creator: Englert, Gerald W.; Wasserbauer, Joseph F. & Whalen, Paul
Partner: UNT Libraries Government Documents Department
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Boundary-Layer Transition at High Reynolds Numbers as Obtained in Flight of a 20 Degree Cone-Cylinder With Wall to Local Stream Temperature Ratios Near 1.0

Description: Boundary-layer transition data at low ratios of wall to local stream temperature have been obtained during the free flight of a highly polished cone-cylinder to a maximum Mach number of 5.02 A maximum transition Reynolds number of 32 x 10(exp 6) occurred at a distance of 25.84 inches from the cone apex. The temperature ratio at transition for a local Mach number of 4.0 was approximately 1.30 as compared with theoretical infinite stability solutions of 1.47 and 1.65 by Dunn and Lin (three-dimens… more
Date: November 3, 1955
Creator: Rabb, Leonard & Disher, John H.
Partner: UNT Libraries Government Documents Department
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Effects of various modifications on the static longitudinal stability and control characteristics of a 0.065-scale model of the Chance Vought Regulus II missile at a Mach number of 2.01: TED No. NACA AD 398

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects on the static longitudinal stability and control characteristics of various modifications to a 0.065-scale model of the Chance Vought Regulus II missile. Some of the modifications included control housing on top of the fuselage, two sizes of canard surfaces with fixed incidence angles, various angles of nose droop, and two types of inlet boundary-layer bleed diverters.
Date: September 26, 1955
Creator: Robinson, Ross B. & Driver, Cornelius
Partner: UNT Libraries Government Documents Department
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