Technical Report Archive & Image Library (TRAIL) - 181 Matching Results

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A special method for finding body distortions that reduce the wave drag of wing and body combinations at supersonic speeds

Description: Report presenting a consideration of the problem of shaping an adjoining fuselage for a given wing and supersonic Mach number so that the combination will have a low wave drag. Only fuselages that can be simulated by singularities distributed along the body axis are studied.
Date: May 20, 1955
Creator: Lomax, Harvard & Heaslet, Max A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Transonic Wind-Tunnel Investigation of Effects of Windshield Shape and Canopy Location on the Aerodynamic Characteristics of Canopy-Body Combinations

Description: "Aerodynamic data have been obtained for a fuselage forebody alone and for canopy-body configurations consisting of four different canopies mounted on a fuselage forebody. Two of the canopies had the same shape and size rearward of the windshield but one had a "flat" and the other a "vee" windshield. The remaining two canopies were located at different body stations and were geometrically similar. The data indicated that the drag of the flat-windshield model was consistently lower than that of … more
Date: September 20, 1955
Creator: Cornette, Elden S. & Robinson, Harold L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison Between Analytical and Wind-Tunnel Results on Flutter of Several Low-Aspect-Ratio, High-Density, Unswept Wings at High Subsonic Speeds and Zero Angle of Attack

Description: Memorandum presenting experimental flutter Mach numbers for several solid, thin, rectangular cantilever wings with uniform section properties, low aspect ratio, and high relative density estimated from the results of previous tests at zero angle of attack. The experimental values are considered estimates, rather than determinations, in the high subsonic speed range because in that range the amplitude criterion was necessarily arbitrary. Results regarding conservatism of standard analysis relati… more
Date: September 20, 1955
Creator: Warner, Robert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Wing Size and Amount of Indentation on Applicability of Transonic Area Rule to Swept-Wing Configurations

Description: Memorandum presenting a systematic transonic zero-lift drag investigation utilizing a swept-wing configuration with three different ratios of wing to fuselage size utilizing a 6-inch helium gun. The experiments and comparisons with other results indicated that the reduction of pressure drag obtainable from partial indentation is approximately proportional to the amount of indentation employed up to a Mach number of 1.3. Results regarding the basic data, total drag, pressure drag, equivalent bod… more
Date: July 20, 1956
Creator: Hall, James Rudyard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics and pressure distributions of a 6-percent-thick 49 degree sweptback wing with blowing over half-span and full-span flaps

Description: From Introduction: "The investigation reported herein was initiated to define further the effects on the aerodynamic characteristics and load distribution of a thin, sweptback wing of a low-pressure blowing system and also to provide information on which to base a more thorough study of a complete airplane configuration."
Date: September 20, 1955
Creator: Whittle, Edward F., Jr. & McLemore, H. Clyde
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation to Mach number 2.0 of shock-positioning control systems for a variable-geometry inlet in combination with a J34 turbojet engine

Description: Report presenting shock-position controls designed to actuate the translating spike and variable bypass of a variable-geometry inlet in the 8- by 6-foot supersonic tunnel. The operation of the inlet was observed in combination with a J34 turbojet engine at a range of Mach numbers. Results regarding terminal-shock-positioning control systems and combination control are provided.
Date: December 20, 1954
Creator: Leissler, L. Abbott & Nettles, J. Cary
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Steady-state and surge characteristics of a compressor equipped with variable inlet guide vanes operating in a turbojet engine

Description: Report presenting an investigation of a turbojet engine with variable inlet guide vanes in an altitude test facility to determine the steady-state compressor performance and surge characteristics. Compressor surge pressure ratios were found to be unaffected by changes in flight condition for either position of the inlet guide vanes. Decreasing the inlet Reynolds number was found to reduce the corrected fuel flow required for compressor surge.
Date: June 20, 1955
Creator: Wallner, Lewis E. & Lubick, Robert J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind pressure distributions at low lift for the XF-92A delta-wing airplane at transonic speeds

Description: Report presenting chordwise pressure distributions measured over the left wing of a Convair XF-92A delta-wing airplane at low lift to determine the effect of Mach number on the wing characteristics at transonic speeds. The critical Mach number of the basic wing was 0.83 for an airplane normal-force coefficient at 0.09. The spanwise load distributions were roughly triangular in shape.
Date: October 20, 1954
Creator: Keener, Earl R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of the Aerodynamic Characteristics at High Supersonic Mach Numbers of a Family of Delta Wings Having Double-Wedge Sections With the Maximum Thickness at 0.18 Chord

Description: Report presenting a program to investigate the aerodynamic characteristics of a family of delta wings with a blunt double-wedge section in the hypersonic tunnel at Mach number 6.9. The wings varied at semiapex angle and were tested over a range of angles of attack and Reynolds numbers. Results regarding lift and drag characteristics, center of pressure and moment coefficient, Schlieren photographs, and surface film flow studies are presented.
Date: October 20, 1954
Creator: Bertram, Mitchel H. & McCauley, William D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Influence of Surface Injection on Heat-Transfer and Skin Friction Associated With the High-Speed Turbulent Boundary Layer

Description: Memorandum presenting a correlation of analyses of the effect of distributed surface injection on the heat transfer and skin friction associated with the turbulent boundary layer at high speeds to eliminate the effects of Mach and Reynolds number. Data for heat transfer and skin friction at three Mach numbers are compared with the analyses and the agreement is good.
Date: February 20, 1956
Creator: Rubesin, Morris W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation to Determine Effects of Center-of-Gravity Location on the Transonic Flutter Characteristics of a 45 Degree Sweptback Wing

Description: Report presenting an experimental investigation in the transonic blowdown tunnel to determine effects of center-of-gravity location on the transonic flutter characteristics of a 45 degree sweptback-wing plan form of aspect ratio 4.0 and taper ratio 0.6. Solid-construction models with streamwise NACA 65A004 airfoil sections and center-of-gravity locations at three different chords were fluttered at a range of Mach numbers.
Date: February 20, 1956
Creator: Jones, George W., Jr. & Unangst, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tank investigation of the hydrodynamic characteristics of a 1/3.33-scale jet-powered dynamic model of the Martin XP6M-1 flying boat with a revised forebody planing bottom : TED No. NACA DE 385

Description: From Summary: "Hydrodynamic characteristics have been determined for a 1/13.33-scale jet-powered dynamic model of the Martin XP6M-1 flying boat with the forebody modified so as to increase the depth of step and the angle between the forebody and afterbody keels. Longitudinal stability during takeoff and landing in smooth water and resistance of the complete model in smooth water and in waves are presented."
Date: October 20, 1955
Creator: Blanchard, Ulysse J. & Carter, Arthur W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Test of NACA FR-1-B, a Low-Acceleration Rocket-Propelled Vehicle for Transonic Flutter Research

Description: Report presenting testing of a low-acceleration transonic flutter test vehicle to obtain flutter data on two similar sweptback wings which indicated that wing flutter was symmetrical in mode. Results regarding flight and flutter characteristics for the FR-1-B are provided.
Date: July 20, 1948
Creator: Angle, Ellwyn E.; Clevenson, Sherman A. & Lundstrom, Reginald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effect of rate of change of angle of attack on the maximum lift coefficient of a pursuit airplane

Description: Report presenting an investigation of the effect of the rate of change of angle of attack on the maximum lift coefficient of a pursuit airplane equipped with a low-drag-type wing in stalls of varying abruptness over a range of Mach and Reynolds numbers. Maximum lift coefficients were found to increase linearly with increasing rate of change of angle of attack per chord length of travel up to the maximum rate attained in the tests.
Date: January 20, 1949
Creator: Gadeberg, Burnett L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Dynamic Response of Turbine-Blade Temperature to Exhaust-Gas Temperature for Gas-Turbine Engines

Description: "The frequency of blade temperature to exhaust gas temperature is presented for two locations in the blade and at several operating conditions. The frequency response was determined by Fourier analysis of transient data. Two analytical methods are presented, and results are compared with experimental data. Dynamic response of turbine-blade temperature to exhaust-gas temperature exhibited the form of an approximate first-order lag" (p. 1).
Date: February 20, 1952
Creator: Hood, Richard & Phillips, William E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Skin-friction drag and boundary-layer transition on a parabolic body of revolution (NACA RM-10)at a Mach number of 1.6 in the Langley 4-by-4 foot supersonic pressure tunnel

Description: Report presenting an investigation at Mach number 1.6 and a range of Reynolds number of the skin-friction drag and boundary-layer transition of a body of revolution. The body had a parabolic-arc profile, a blunt base, and a fineness ratio of 12.2 (NACA RM-10). Results regarding the effect of surface condition, drag breakdown, and results of boundary-layer surveys are provided.
Date: May 20, 1952
Creator: Czarnecki, K. R. & Marte, Jack E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of rotor-and stator-blade modifications on surge performance of an 11-stage axial-flow compressor 1: original production compressor of XJ40-WE-6 engine

Description: Report presenting an investigation to increase the compressor surge-limit pressure ratio of the XJ40-WE-6 turbojet engine at high equivalent speeds. The two compressor modifications investigated included twisting rotor blades to change blade section angles and inserting new stator diaphragms with different blade angles. Results regarding the effect of surge limit on engine performance, performance map of original compressor with mixer, effect of blade modifications on surge line, effect of mixe… more
Date: May 20, 1953
Creator: Finger, Harold B.; Essig, Robert H. & Conrad, E. William
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation From Mach Number 0.8 to 2.0 to Determine Some Effects of Wing-to-Tail Distance on the Longitudinal Stability and Control Characteristics of a 60 Degree Delta-Wing-Canard Missile

Description: Report presenting a flight investigation using rocket-powered models to determine some of the effects of wing-to-tail distance on the stability and control characteristics of a canard-missile configuration with 60 degree delta wings and control surfaces. Both models were tested over a range of Mach numbers from 0.8 to 2.0, and canard hinge moment and model drag data are presented. Testing indicated that additional fuselage length increases the lift-curve slope slightly and has very little effec… more
Date: June 20, 1952
Creator: Brown, Clarence A., Jr. & Lundstrom, Reginald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Investigation of the Low-Amplitude Damping in Pitch of Tailless Delta- and Swept-Wing Configurations at Mach Numbers From 0.7 to 1.35

Description: Report presenting a flight investigation using four rocket-propelled models of low-aspect-ratio tailless configurations between Mach numbers 0.7 and 1.35. The configurations investigated were a 45 degree delta model with NACA 63A010 airfoil sections parallel to free stream, a 45 degree delta-wing model with NACA 63A006 airfoil sections parallel to free stream, a 37.5 degree swept-tapered wing model with NACA 64(sub 1)A012 sections perpendicular to quarter chord, and a 39 degree swept-tapered-wi… more
Date: August 20, 1952
Creator: D'Aiutolo, Charles T. & Parker, Robert N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analytical comparison of turbine-blade cooling systems designed for a turbojet engine operating at supersonic speed and high altitude 1: liquid-cooling systems

Description: Report presenting an investigation of the influence of high-altitude supersonic flight on the operation and effectiveness of turbine-blade liquid-cooling systems for application in turbojet engines in guided missiles and in supersonic aircraft. The problems encountered in liquid-cooling systems were investigated with reference to several specific designs for alternate heat-rejection mediums.
Date: February 20, 1953
Creator: Schramm, Wilson B.; Nachtigall, Alfred J. & Arne, Vernon L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests in the Ames 40- by 80-Foot Wind Tunnel of an Airplane Model With an Aspect Ratio 4 Triangular Wing and an All-Movable Horizontal Tail - High-Lift Devices and Lateral Controls

Description: Memorandum presenting tests of a triangular-wing-airplane model equipped with high-lift devices and lateral and directional controls. The model consisted of an aspect ratio 4 triangular wing in combination with a fuselage of fineness ratio 12.5, a thin, triangular, vertical tail with a constant-chord rudder, and a thin, unswept, all-movable horizontal tail. Results regarding the effects of flap deflection and tail incidence on the pitching moment characteristics, lift and drag characteristics, … more
Date: February 20, 1953
Creator: Franks, Ralph W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Temperature response of turbine-blade metal covered with oxide coatings supplied by fuel additives

Description: Report presenting an investigation to determine the effects of turbine-blade coatings, supplied by fuel additives, on heat transfer with combustor exhaust gases to an S-816 alloy blade. Two fuel additives were used. The results indicated that the fuel additives provided an oxide coating on the combustor-liner wall and other metal parts, including the blade, exposed to the exhaust gas.
Date: August 20, 1952
Creator: McCafferty, Richard J. & Butze, Helmut F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Total-Pressure and Schlieren Studies of the Wakes of Various Canard Control Surfaces Mounted on a Missile Body at a Mach Number of 1.93

Description: Report presenting wind-tunnel studies of the wake behind eight types of canard control surfaces of equal span mounted on a missile body at Mach number 1.93. The effect of simulated external rocket boosters on the pressure field was also determined for three control-surface plan forms. The investigation also included the effect of end plates attached to the tips of one of the controls surfaces.
Date: November 20, 1952
Creator: Boatright, William B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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