Technical Report Archive & Image Library (TRAIL) - 342 Matching Results

Search Results

Results: 1 - 24 next
open access

Adaptation of a Cascade Impactor to Flight Measurement of Droplet Size in Clouds

Description: "A cascade impactor, an instrument for obtaining the size distribution of droplets borne in a low-velocity air stream, was adapted for flight cloud droplet-size studies. The air containing the droplets was slowed down from flight speed by a diffuser to the inlet-air velocity of the impactor" (p. 1).
Date: September 18, 1951
Creator: Levine, Joseph & Kleinknecht, Kenneth S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Additional results of an investigation at transonic speeds to determine the effects of a heated propulsive jet on the drag characteristics of a series of related afterbodies

Description: From Introduction: "Presented in this report are the basic data obtained from investigation. The data are presented with limited analysis in order to expedite their availability to those concerned with jet-exit-afterbody design."
Date: September 24, 1956
Creator: Henry, Beverly Z., Jr. & Cahn, Maurice S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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
open access

Aerodynamic characteristics at Mach numbers from 0.7 to 1.75 of a four-engine swept-wing airplane configuration as obtained from a rocket-propelled model test

Description: Report presenting flight testing of a rocket-propelled model of a typical multiengine airplane configuration to obtain data on drag, stability, and nacelle performance. Data were obtained at a variety of Mach numbers, lift coefficients, and subsonic and supersonic speeds. Results regarding airplane performance, nacelle performance, longitudinal characteristics, and lateral characteristics are provided.
Date: September 2, 1955
Creator: Chapman, Rowe, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics at Mach Numbers From 2.5 to 3.5 of a Canard Bomber Configuration Designed for Supersonic Cruise Flight

Description: Report presenting an investigation of a canard-type configuration designed for supersonic cruise flight in the Unitary Plan wind tunnel. Tests were conducted over a range of angles of attack and angles of sideslip. Results regarding the effect of forebody configuration, effects of Reynolds number and transition, effect of canard and elevon deflection, and effect of vertical surfaces are provided.
Date: September 10, 1958
Creator: Carmel, Melvin M.; Kelly, Thomas C. & Gregory, Donald T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic characteristics at transonic speeds of a 60 degree delta wing equipped with a constant-chord flap-type control with and without an unshielded horn balance: transonic-bump method

Description: Report presenting an investigation to determine the control hinge moments and effectiveness at transonic speeds of a delta wing equipped with a constant-chord flap-type control with and without an unshielded triangular horn balance in the 7- by 10-foot tunnel using the transonic-bump method. The data indicated that the horn balance control was consistently more effective in changing lift at all Mach numbers than was the plain control but there was no appreciable difference in pitching-moment ef… more
Date: September 16, 1952
Creator: Wiley, Harleth G. & Zontek, Leon
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Aerodynamic Characteristics at Transonic Speeds of an All-Movable, Tapered, 45 Degree Sweptback, Aspect-Ratio-4 Tail Deflected About a Skewed Hinge Axis and Equipped with an Inset Unbalancing Tab

Description: From Introduction: "The present investigation presents the lift and moment characteristics of an aspect-ratio-4.0 tail, sweptback 45^o at the quarter-chord line and pivoted about an axis sweptback 55.5^o and passing through the leading edge of the root-chord line."
Date: September 29, 1953
Creator: Watson, James M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102A Airplane at Mach Numbers of 1.41, 1.61, and 2.01

Description: "Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41, 1.61, and 2.01 of various arrangements of a 0.04956-scale model of the Convair F-102A airplane with faired inlets. Tests made of the model equipped with a plain wing, a wing with 6.4 percent conical camber, and a wing with 15 percent conical camber. Body modifications including an extended nose, a modified canopy, and extended afterbody fillets were evaluated" (p. 1).
Date: September 30, 1955
Creator: Spearman, M. Leroy & Driver, Cornelius
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic characteristics of the NACA RM-10 research missile in the Ames 1- by 3-foot supersonic wind tunnel no. 2: Pressure and force measurements at Mach numbers of 1.52 and 1.98

Description: Report presenting an experimental investigation of the aerodynamic characteristics of a fin-stabilized body of revolution, designated as RM-10, in a supersonic wind tunnel. Pressure distributions and force characteristics were determined at two different Mach numbers. Results regarding pressure distributions, body-alone force tests, and body-tail combination force tests are provided.
Date: September 19, 1951
Creator: Perkins, Edward W.; Gowen, Forrest E. & Jorgensen, Leland H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic heat transfer and zero-lift of a flat windshield canopy on the NACA RM-10 research vehicle at high Reynolds numbers for a flight Mach number range from 1.5 to 3.0

Description: Report presenting the aerodynamic heat-transfer properties and zero-lift drag of a typical pilot's canopy as determined by a rocket-model flight test through a range of Mach and Reynolds numbers. The canopy had a 63 degree sweptback flat windshield, circular cross section, and an equivalent body fineness ratio of 7.0. Results regarding the canopy temperature distribution, canopy pressure distribution, heat-transfer coefficient, and drag are provided.
Date: September 26, 1956
Creator: Hoffman, Sherwood & Chauvin, Leo T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic heating of a wing as determined from a free-flight rocket-model test to Mach number 3.64

Description: From Introduction: "The primary purpose of the wing instrumentation was to obtain data for use in design of NACA research missiles; however, it is believed that the wing is representative of typical supersonic designs and that the data will be of general use and interest. Only the wing data are reported herein."
Date: September 11, 1956
Creator: Swanson, Andrew G. & Rumsey, Charles B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Load Measurements Over a Leading-Edge Slat on a 40 Degree Sweptback Wing at Mach Numbers From 0.10 to 0.91

Description: Report presenting an investigation of the aerodynamic loads on a leading-edge slat on a 40 degree sweptback wing with NACA 64(sub 1)-112 airfoil sections in the low-turbulence pressure tunnel. Results regarding wing force data, slat force data, and slat pressure distributions are provided.
Date: September 23, 1952
Creator: Cahill, Jones F. & Nuber, Robert J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Performance and Static Stability and Control of Flat-Top Hypersonic Gliders at Mach Numbers From 0.6 to 18

Description: Memorandum presenting a study of aerodynamic performance and static stability and control at hypersonic speeds. In the first part of the study, the effect of interference lift is investigated by tests of asymmetric models with conical fuselages and arrow plan-form wings. In the second part, the aerodynamic performance and static stability and control characteristics of a hypersonic glider are investigated in somewhat greater detail.
Date: September 17, 1958
Creator: Syvertson, Clarence A.; Gloria, Hermilo R. & Sarabia, Michael F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Performance of Several Techniques for Spike-Position Control of a Blunt-Lip Nose Inlet Having Internal Contraction; Mach Numbers of 0.63 and 1.5 to 2.0

Description: Memorandum presenting a study to determine locations of pressure sensors for controlling the spike position of a blunt-lip, axisymmetric inlet with internal contraction. The inlet performance was determined at Mach numbers of 0.63 and 1.5 to 2.0 for airflow schedules corresponding to those of a given turbojet engine over a wide range of ambient temperatures. The use of the ratio of a throat static pressure to either a local total or the spike-tip total pressure provided a signal that could set … more
Date: September 17, 1957
Creator: Anderson, Arthur A. & Weinstein, Maynard I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effect of sideslip on aerodynamic characteristics at a Mach number of 1.4 with the wing twisted and cambered

Description: Report presenting the longitudinal and lateral characteristics of a wing-fuselage combination with a wing with the leading edge swept back 63 degrees and cambered and twisted for a uniform load at lift coefficient 0.25 and Mach number 1.5. The investigation occurred over a range of sideslip angles. The results indicated that the longitudinal characteristics were essentially unaffected by Reynolds number or the sideslip angles investigated.
Date: September 29, 1950
Creator: Lessing, Henry C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aeronautical Characteristics of a 45 Degree Sweptback Wing-Fuselage Combination and the Fuselage Alone Obtained in the Langley 8-Foot Transonic Tunnel

Description: Report presenting a fuselage and wing-fuselage combination with a wing of 45 degrees sweepback of the 0.25-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil sections in the slotted test section of a transonic tunnel for a range of Mach numbers and angles of attack. Results regarding lift characteristics, drag characteristics, lift-drag ratios, pitching-moment characteristics, a comparison with other test results, and base-pressure characteristics are provided.
Date: September 16, 1952
Creator: Osborne, Robert S. & Mugler, John P., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An air-borne target simulator for use in optical sight tracking studies

Description: From Introduction: "The development of this air-borne optical target simulator and the results of evaluation flight tests (including a comparison of airplane tracking performance against the simulated and an actual target airplane) are presented herein."
Date: September 1, 1955
Creator: Doolin, Brian F.; Smith, G. Allan & Drinkwater, Fred J., III
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude investigation of three flame-holder and fuel-systems configurations in a short converging afterburner on a turbojet engine

Description: From Introduction: "Previous investigations of a number of internal configurations in the same afterburner shell are reported in reference 1 and 2. In the investigation reported herein, the performance and operational characteristics of three afterburner internal configurations were evaluated."
Date: September 10, 1952
Creator: Braithwaite, Willis M.; Renas, Paul E. & Jansen, Emmert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude performance characteristics of the J47-25 turbojet engine: data presentation

Description: From Introduction: "An investigation was conducted in an NACA Lewis altitude chamber to determine the altitude performance characteristics of a J47-25 axial-flow turbojet engine over a range of engine-inlet Reynolds number indices corresponding to altitudes from 18,000 to 54,000 feet and flight Mach numbers from 0.50 to 1.10. Reynolds number at a given corrected engine speed and is a function only of engine-inlet total pressure and temperature, was used instead of various set altitudes and flig… more
Date: September 29, 1953
Creator: Renas, Paul E. & Jansen, Emmert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude-Wind-Tunnel Investigation of Performance Characteristics of a J47D Prototype (RX1-1) Turbojet Engine With Fixed-Area Exhaust Nozzle

Description: Report presenting an investigation to determine the overall performance of a prototype model of the J47D (RX1-1) turbojet engine with a fixed-area exhaust nozzle. Data was obtained for a range of engine speeds, altitudes, and Mach numbers. Results regarding the effect of those variables and generalization in terms of pumping characteristics are provided.
Date: September 4, 1951
Creator: Saari, M. J. & Wintler, J. T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude-Wind-Tunnel Investigation of Performance Characteristics of a J47D Prototype (RX1-1) Turbojet Engine With Variable-Area Exhaust Nozzle

Description: Performance of a J47D (RX1-1) turbojet engine equipped with afterburner, variable-area exhaust nozzle, and integrated electronic control was determined over a range of flight conditions. These data were obtained with the electronic control both operative and inoperative. For operation with scheduled exhaust nozzle area, the minimum specific fuel consumption of 1.15 pounds of fuel per hour per pound of net thrust occurred at about 7200 rpm at altitudes from 5000 to 25,000 feet at a flight Mach n… more
Date: September 5, 1951
Creator: Conrad, E. William & McAulay, John E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude-Wind-Tunnel Investigation of Turbine Performance in J47 Turbojet Engine

Description: From Introduction: "Performance data are presented in this report to show the characteristics of the turbine operating as an integral part of the engine. Typical results are graphically presented to show the effects of changes in altitude, flight Mach number, and exhaust-nozzle-outlet area on turbine performance. All turbine-performance data obtained are given in tabular form."
Date: September 21, 1950
Creator: Thorman, H. Carl & McAulay, John E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aluminum borohydride as an ignition source for turbojet combustors

Description: From Introduction: "Problems associated with the use of aluminum borohydride for ignition in aircraft are discussed. A detailed description of its properties and results of static chamber tests to determine the effect of diluting aluminum borohydride with n-pentane on flammability in dry air are included in this investigation."
Date: September 3, 1953
Creator: Straight, David M.; Fletcher, Edward A. & Foster, Hampton H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen