Technical Report Archive & Image Library (TRAIL) - 50 Matching Results

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Theoretical Investigation of the Effects of the Artificial-Feel System on the Maneuvering Characteristics of the F-89 Airplane

Description: The possibility of overshooting the anticipated normal acceleration as a result of the artificial-feel characteristics of the F-89C airplane at a condition of minimum static stability was investigated analytically by means of an electronic simulator. Several methods of improving the stick-force characteristics were studied. It is shown that, due to the lag in build-up of the portion of the stick force introduced by the bobweight, it would be possible for excessive overshoots of normal accelerat… more
Date: December 31, 1952
Creator: Abramovitz, Marvin; Schmidt, Stanley F. & Belsley, Steven E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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High Speed Stability and Control Characteristics of a 0.17-Scale Model of the McDonnell XF2H-1 Airplane (TED No. NACA DE 318)

Description: "High-speed wind-tunnel tests were conducted of two versions of a 0.17-scale model of the McDonnell XF2H-1 airplane to ascertain the high-speed stability and control characteristics and to study means for raising the high-speed buffet limit of the airplane, The results for the revised model, employing a thinner wing and tail than the original model, revealed a mild diving tendency from 0.75 to 0.80 Mach number, followed by a marked climbing tendency from 0.80 to 0.875 Mach number. The high-spee… more
Date: March 31, 1949
Creator: Axelson, John A. & Emerson, Horace F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effects of various parameters including Mach number on propeller blade flutter with emphasis on stall flutter

Description: Report presenting an investigation of the effects of many of the parameters significant to wing flutter on several untwisted rotating models to determine their significance with respect to stall flutter of propeller blades. The parameters included torsional stiffness, section thickness ratio, sweepback, length-chord ratio, section center-of-gravity location, blade taper, Mach number, and fluid density. Results regarding the considerations on method of presentation, experimental data and discuss… more
Date: January 31, 1951
Creator: Baker, John E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Rocket-Model Measurements of Zero-Lift Damping in Roll of the Bell MX-776 Missile at Mach Numbers from 0.6 to 1.56

Description: The zero-lift damping in roll of the Bell MX-776 missile has been measured by a sting-mounted rocket-model technique at Mach numbers from 0.6 to 1.56. The damping-in-roll data, in general, show no unusual variation with Mach number. Aileron rolling-moment effectiveness derived from these data and previously obtained rolling-effectiveness data appear reasonable,.
Date: December 31, 1953
Creator: Bland, William M., Jr. & Purser, Paul E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Longitudinal Stability and Afterbody Pressure Characteristics of Specialized Store Configurations at Transonic Speeds

Description: Report presenting an investigation to determine the longitudinal stability and afterbody pressure characteristics of the TX-14 and TX-16 special weapons at transonic and supersonic speeds. Results regarding dynamic testing and pressure testing are provided.
Date: March 31, 1954
Creator: Braden, John A. & Henry, Beverly Z., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effects of fences on the high-speed longitudinal stability of a swept-wing airplane

Description: Report presenting a series of fence installations tested on a swept-wing jet airplane to determine their effects on the longitudinal instability, or "pitch-up", encountered in high-maneuvering flight. Longitudinal-stability measurements were made at a variety of Mach numbers with nine fence configurations that varied in chordwise extent and spanwise position. Results regarding longitudinal stability, flow phenomena, buffeting and wing dropping, drag, and low-speed stalls are provided.
Date: August 31, 1953
Creator: Bray, Richard S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Heat Transfer on the Lifting Surfaces of a 60 Degree Delta Wing at Angle of Attack for Mach Number 1.98

Description: Report presenting the heat transfer and pressures on the lifting surfaces of a 60 degree delta wing with NACA 65A005 profile at angles of attack up to 9 degrees. Results obtained are compared to values obtained from flat-plate theory.
Date: May 31, 1956
Creator: Carter, Howard S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pressure distribution and pressure drag for a hemispherical nose at Mach numbers 2.05, 2.54, and 3.04

Description: Report presenting an experimental investigation of the pressure distributions on a hemispherical nose 3.98 inches in diameter, mounted on a cylindrical support, at several Mach and Reynolds numbers. The Reynolds number was based on body diameter and free-stream conditions. Pressure-drag coefficients were calculated and good agreement was obtained with other testing.
Date: December 31, 1952
Creator: Chauvin, Leo T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lift, Drag, Static Stability, and Buffet Boundaries of a Model of the McDonnell F3H-1N Airplane at Mach Numbers from 0.40 to 1.27, TED No. NACA DE 351

Description: "The National Advisory Committee for Aeronautics has conducted a flight test of a model approximating the McDonnell F3H-1N airplane configuration to determine its pitch-up and buffet boundaries, as well as the usual longitudinal stability derivatives obtainable from the pulsed- tail technique. The test was conducted by the freely flying rocket-boosted model technique developed at the Langley Laboratory; results were obtained at Mach numbers from 0.40 to 1.27 at corresponding Reynolds numbers of… more
Date: January 31, 1956
Creator: Crabill, Norman L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of the NACA 1.167-(0)(03)-058 and NACA 1.167-(0)(05)-058 Three-Blade Propellers at Forward Mach Numbers to 0.92 Including Effects of Thrust-Axis Inclination

Description: Report presenting an investigation to determine the aerodynamic characteristics of two three-blade propellers over a range of blade angles and Mach numbers. The thick-blade propeller was more adversely affected by compressibility than the thin-blade propeller, and the maximum efficiency of the thin-blade propeller was higher than the thick-blade propeller.
Date: August 31, 1953
Creator: Demele, Fred A. & Otey, William R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Application of blade cooling to gas turbines

Description: From Summary: "A review of the status of the knowledge on turbine-blade cooling and a description of pertinent NACA investigations are presented. The current limitations in performance of uncooled and cooled engines are briefly discussed. Finally, the knowledge available and investigations to increase the knowledge on heat transfer, cooling-flow, and performance characteristics of cooled turbines are discussed."
Date: May 31, 1950
Creator: Ellerbrock, Herman H., Jr. & Schafer, Louis J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Supersonic-Tunnel Tests of Two Supersonic Airplane Model Configurations

Description: Report presenting supersonic-tunnel tests of two models of similar supersonic airplane configurations at Mach numbers of 1.55, 1.90, and 2.32 to determine values of the drag, lift, pitching moment, yawing moment, and side force. The models were similar except for the vertical wing location relative to the body axis and horizontal tail; one had a high wing and one had a low wing. Results regarding the precision of data, Reynolds numbers of tests, results at the different Mach numbers, and Schile… more
Date: December 31, 1947
Creator: Ellis, Macon C., Jr.; Hasel, Lowell E. & Grigsby, Carl E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Determination of the Lateral Handling Qualities of the Bell X-5 Research Airplane at 58.7 Degrees Sweepback

Description: Memorandum presenting the Bell X-5 variable-sweep research airplane tested primarily at 58.7 degrees sweepback to determine the characteristics at transonic speeds of a fighter-type airplane with extreme sweepback. Some of the dynamic and static lateral stability characteristics have been discussed previously. Results regarding the lateral control, roll coupling, lateral problems at high lift, wing dropping, rudder oscillation at supersonic Mach numbers, and some pilots' impressions are also pr… more
Date: May 31, 1956
Creator: Finch, Thomas W. & Walker, Joseph A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary evaluation of the air and fuel specific-impulse characteristics of several potential ram-jet fuels 4: hydrogen, a-methylnaphthalene, and carbon

Description: A preliminary analytical evaluation of the air and fuel specific-impulse characteristics of hydrogen, a-methylnapthalene, and graphite carbon has been made. Adiabatic constant-pressure combustion flame temperatures for each fuel at several equivalence ratios were calculated for an initial air temperature of 560 degrees R and a pressure of 2 atmospheres.
Date: August 31, 1951
Creator: Gammon, Benson E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurement of Static Forces on Externally Carried Bombs of Fineness Ratios 7.1 and 10.5 in the Flow Field of a Swept-Wing Fighter- Bomber Configuration at a Mach Number of 1.6

Description: Memorandum presenting forces and moments measured at Mach number 1.6 in the 4- by 4-foot supersonic pressure tunnel on bombs of fineness ratios 7.0 and 10.5 in the presence of a swept-wing fighter-bomber airplane configuration for a large number of positions under the fuselage. The results can be used to calculate bomb-drop paths.
Date: January 31, 1957
Creator: Geier, Douglas J. & Carlson, Harry W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Results of an Altitude-Wind-Tunnel Investigation of a TG-100A Gas Turbine-Propeller Engine 5 - Combustion-Chamber Characteristics

Description: "An investigation to determine the performance and operational characteristics of the TG-1OOA gas turbine-propeller engine was conducted in the Cleveland altitude wind tunnel. As part of this investigation, the combustion-chamber performance was determined at pressure altitudes from 5000 to 35,000 feet, compressor-inlet rm-pressure ratios of 1.00 and 1.09, and engine speeds from 8000 to 13,000 rpm. Combustion-chamber performance is presented as a function of corrected engine speed and corrected… more
Date: December 31, 1947
Creator: Gensenheyner, Robert M. & Berdysz, Joseph J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of inlet oxygen concentration on combustion efficiency of J33 single combustor operating with gaseous propane

Description: Report presenting an investigation to determine the effect of oxygen concentration of the inlet oxygen-nitrogen mixture on the combustion efficiency of a J33 single combustor operating with gaseous propane fuel. Combustion efficiency data were obtained at a variety of combustion-inlet total pressures, fuel flow rates, and inlet oxygen concentrations. Results regarding combustor data, application of fundamental combustion properties to combustor data, application of simplified reaction kinetics … more
Date: March 31, 1953
Creator: Graves, Charles C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Nose Shape and Wing Thickness Ratio on the Drag at Zero Lift of a Missile Having Triangular Wings and Tails

Description: "Free-flight tests have been made to determine the drag at zero lift of several configurations of a missile having triangular wings and tails. Base-pressure measurements were also obtained for some of the configurations. The results show that increasing the wing thickness ratio from 4 to 6 percent increased the wing drag by about 100 percent at M = 1.3 and by about 30 percent at M = 1.8" (p. 1).
Date: May 31, 1950
Creator: Hall, James R. & Sandahl, Carl A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A summary of NACA research on the strength and creep of aircraft structures at elevated temperatures

Description: Report summarizing research on the strength and creep of aircraft structural elements and components at elevated temperatures. Experimental data for aluminum alloy columns, plates, stiffened panels, and multiweb box beams are presented for temperatures up to 600 degrees Fahrenheit and compared with results predicted from materials data.
Date: May 31, 1956
Creator: Heldenfels, Richard R. & Mathauser, Eldon E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation at Transonic Speeds of the Effects of Fences, Drooped Nose, and Vortex Generators on the Aerodynamic Characteristics of a Wing-Fuselage Combination Having a 6-Percent-Thick, 45 Degree Sweptback Wing

Description: Report presenting an investigation at transonic speeds to determine the effects of fences, drooped nose, combination fences and drooped nose, and vortex generators on a 45 degree sweptback wing-fuselage combination. The purpose of undertaking this investigation was due to the pitch-up tendency that results from leading-edge vortex-type flow on thin sweptback wings. The data for each component and their interaction with one another is also provided.
Date: March 31, 1953
Creator: Hieser, Gerald
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

High-Speed Aerodynamic Characteristics of Four Thin NACA 63-Series Airfoils

Description: Memorandum presenting high-speed wind-tunnel tests of four thin NACA 63-series airfoil sections with a design lift coefficient of 0.2 with the uniform-load type of mean camber line to determine the effectiveness of forward movement of the minimum-pressure position in improving the high-speed lift characteristics of low-drag airfoils. Results regarding the tunnel-wall effects, lift coefficient, drag coefficient, and moment coefficient are provided.
Date: December 31, 1947
Creator: Ilk, Richard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation at high subsonic speeds of a 45 sweptback horizontal tail with plain and horn-balanced control surfaces

Description: Report presenting an investigation in the 7- by 10-foot tunnel of the aerodynamic and hinge-moment characteristics of an untapered, aspect ratio 3, semispan horizontal-tail model with 45 degrees of sweepback through a range of Mach numbers. The model was equipped with an unbalanced and a horn-balanced 25-percent-chord elevator.
Date: March 31, 1950
Creator: Johnson, Harold S. & Thompson, Robert F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of Two Vertical-Takeoff-and-Landing Jet Bomber Airplane Configurations at Mach Numbers of 1.94 and 2.40

Description: Report presenting an investigation to obtain information about the basic aerodynamic characteristics of two vertical-take-off-and-landing jet bomber airplanes, one with a high wing and one with a low wing. Results regarding pitch and sideslip are provided. The high-tail configurations were found to have higher lift-drag ratios for both high- and low-wing models.
Date: October 31, 1956
Creator: Jones, Robert A. & Rainey, Robert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Correlation by the Hypersonic Similarity Rule of the Pressure Distributions and Wave Drags for Minimum-Drag Nose Shapes at Zero Angle of Attack

Description: Memorandum presenting the use of the hypersonic similarity rule to correlate pressure distributions and wave drags for minimum-drag nose shapes derived by Von Karman and Newton. The computed results have been confirmed by comparison with available experimental data. Wave-drag results for both the Karman and Newtonian shapes are compared with each other and with results for ocnes and circular-arc tangent ogives.
Date: August 31, 1953
Creator: Jorgensen, Leland H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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