Technical Report Archive & Image Library (TRAIL) - 493 Matching Results

Search Results

Results: 1 - 24 next
open access

Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair TF-102A Airplane at Transonic Speeds, Coord. No. AF-120

Description: "The basic aerodynamic characteristics of a 0.04956-scale model of the Convair TF-102A airplane with controls undeflected have been determined at Mach numbers from 0.60 to 1.135 for angles of attack up to approximately 22 deg in the Langley 8-foot transonic tunnel. In addition, comparisons have been made with data obtained from a previous investigation of a 0.04956-scale model of the Convair F-102A airplane. The results indicated the TF-102A airplane was longitudinally stable for all conditions… more
Date: 1957~
Creator: Osborne, Robert S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Low-Speed Investigation of the Magnus Effects on a Sting-Mounted Model of a Typical Mortar Shell

Description: Memorandum presenting an investigation made in the stability tunnel with a 2.3-scale spinning model of a typical mortar shell. The tests were made to measure the aerodynamic forces and moments acting on a typical spinning mortar shell. Results regarding the basic configuration, effect of changes in tail configuration, effect of changes in the nose configuration, and comparison of mortar shell and antisubmarine rocket are provided.
Date: January 2, 1957
Creator: Lichtenstein, Jacob H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Application of a Windshield-Display System to the Low-Altitude Bombing Problem

Description: From Introduction: "The design and flight evaluation of an airborne target simulator for use in tracking studies of fighter-type airplanes equipped with optical gunsights have recently been reported (ref. 1). In this equipment the target airplane was represented by a movable dot of light projected on the windshield of the test airplane."
Date: January 4, 1957
Creator: Barnett, Robert M.; Kauffman, William M. & Fulcher, Elmer C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Transonic Flutter Investigation of Two 64 Degree Delta Wings With Simulated Streamwise Rib and Orthogonal Spar Construction

Description: Report presenting an investigation of the transonic flutter characteristics of two 64 degree sweptback delta wings. Both of the wings had simulated streamwise ribs and orthogonal spanwise spars, but the wings had different stiffness and mass.
Date: January 4, 1957
Creator: Jones, George W., Jr. & Young, Lou S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of the aerodynamic characteristics of a series of swept, highly tapered thin wings at transonic speeds: transonic bumb method

Description: Report presenting an investigation by the transonic-bump method of the static longitudinal aerodynamic characteristics of a series of swept, highly tapered, thin wings in the high-speed 7- by 10-foot tunnel. Testing occurred over a range of Mach and Reynolds numbers and angles of attack. Results regarding lift and drag characteristics and longitudinal stability characteristics are provided.
Date: January 4, 1957
Creator: Few, Albert G., Jr. & Fournier, Paul G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Hinge-Moment and Effectiveness Characteristics of an Aspect-Ratio-8.2 Flap-Type Control on a 60 Degree Delta Wing at Mach Numbers from 0.72 to 1.96

Description: Memorandum presenting an investigation of a semispan-wing-fuselage model with a 60 degree delta wing with an aspect-ratio-8.2 blunt trailing-edge flap-type control in the 9- by 12-inch blowdown tunnel. Control hinge-moment and effectiveness characteristics were obtained over an angle-of-attack range of plus or minus 10 degrees at control deflections up to 90 degrees.
Date: January 7, 1957
Creator: Guy, Lawrence D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Identification of Foreign Objects Damaging Compressor Blades in Turbojet Engines

Description: "Damage to the compressor blades of turbojet engines due to ingestion of foreign objects is a growing problem, the solution of which has been made more difficult by the large percentage of damaging materials that have remained unknown. A rapid emission spectroscopic method was devised to identify the chemical composition of these foreign objects. Results on laboratory-prepared specimens and blades from damaged engines show that the method can be utilized to determine the nature of the ingested … more
Date: January 7, 1957
Creator: Spakowski, A. E. & Graab, J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurements of Runway Roughness of Four Commercial Airports

Description: "Measurements of runway roughness were made on runaways at Washington National Airport, New York International Airport, La Guardia Airport, and Logan International Airport, Boston, Mass. This report presents these measurements in the form of tables as well as plots" (p. 1).
Date: January 7, 1957
Creator: Potter, Dexter M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of an impulse-type supersonic-compressor rotor having a mean turning of 114 degrees

Description: Report presenting testing of the performance of a 16-inch tip-diameter rotor designed for impulse operation at the mean radius with a relative Mach number of 1.53 and 114 degrees of turning. Results regarding the rotor with guide vanes, blade-element performance, rotor alone, and modified rotor hub contour are provided.
Date: January 7, 1957
Creator: Goldberg, Theodore J. & Erwin, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of the Republic F-105 Inlet with Various Modifications at Mach Numbers 1.41, 1.81, and 2.01

Description: "A 1/13-scale Republic F-105 wing-root inlet configuration in which inlet components were varied was tested in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1,41, 1.81, and 2,01 corresponding to Reynolds numbers per foot of 4,19 X 10(exp 6) , 3.74 X 10(exp 6) , and 3.46 x 10(exp 6) respectively. Angles of attack ranged from -4 deg to 15 deg and a few configurations were tested in a sideslip range from -8 deg to 4 deg. Inlet performance and engine-face flow distortions a… more
Date: January 8, 1957
Creator: Robins, A. Warner
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A balanced-pressure sliding seal used for transfer of pressurized air between stationary and rotating parts

Description: A combination sliding-ring and pressure-balancing seal capable of transferring pressurize air from stationary to rotating parts was developed and experimentally investigated at sliding velocities and cooling-air pressures up to 10,000 feet per minute and 38.3 pounds per square inch absolute, respectively. Leakage of cooling air was completely eliminated with an expenditure of balance air less than one-fourth the leakage loss of air from labyrinth seals under the same conditions. Additional cool… more
Date: January 9, 1957
Creator: Curren, Arthur N. & Cochran, Reeves P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Comparison of experimental with theoretical total-pressure loss in parallel-walled turbojet combustors

Description: "An experimental investigation of combustor total-pressure loss was undertaken to confirm previous theoretical analyses of effects of geometric and flow variables and of heat addition. The results indicate that a reasonable estimate of cold-flow total-pressure-loss coefficient may be obtained from the theoretical analyses. Calculated total-pressure loss due to heat addition agreed with experimental data only when there was no flame ejection from the liner at the upstream air-entry holes" (p. 1). more
Date: January 9, 1957
Creator: Dittrich, Ralph T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flutter Characteristics at Transonic Speeds of a 45 Degree Sweptback Wing With and Without Inboard Modifications at the Leading and Trailing Edges

Description: Report presenting flutter characteristics at transonic speeds of a model of a fighter-type-airplane wing over a range of Mach numbers. The results indicated an abrupt increase in flutter speed ratio near a Mach number of 1.0, with only slight increases noted as it was increased to 1.4. Results regarding the effect of flutter-boundary shape are provided.
Date: January 9, 1957
Creator: Sellers, Thomas B. & Land, Norman S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a 0.6 Hub-Tip Radius-Ratio Transonic Turbine Designed for Secondary-Flow Study 1: Design and Experimental Performance of Standard Turbine

Description: Report presenting an investigation of a transonic turbine with a 0.6 hub-tip radius ratio in order to determine the effect of stator and rotor secondary flows on turbine performance. Results regarding the overall performance, stator exit surveys, and rotor exit surveys are provided.
Date: January 9, 1957
Creator: Rohlik, Harold E.; Wintucky, William T. & Scibbe, Herbert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A study of injection processes for liquid oxygen and gaseous hydrogen in a 200-pound-thrust rocket engine

Description: Characteristic velocities of six single-element injectors that separately varied propellant spreading and mixing were measured over a range of oxidant-fuel weight ratios of 2 to 7. Hydrogen inlet temperature was -320 degrees F. Injectors that both mixed and spread the propellants had the highest characteristic-velocity efficiency. Spreading of either propellant produced about the same increment efficiency. The increase in efficiency due to mixing was relatively small. With similar injectors, ox… more
Date: January 9, 1957
Creator: Auble, Carmon M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Static Aerodynamic Forces and Moments at High Subsonic Speeds on a Missile Model During Simulated Launching From the Midsemispan Location of a 45 Degree Sweptback Wing-Fuselage-Pylon Combination

Description: "An investigation was made at high subsonic speeds in the Langley high-speed 7- by 10-foot tunnel to determine the static aerodynamic forces and moments on a missile model during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage-pylon combination. The results indicated significant variations in all the aerodynamic components with changes in chordwise location of the missile. Increasing the angle of attack caused increases in the induced effects on the miss… more
Date: January 10, 1957
Creator: Alford, William J., Jr. & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurement of Static Forces on Internally Carried Bombs of Three Fineness Ratios in Flow Field of a Swept-Wing Fighter-Bomber Configuration at a Mach Number of 1.61 With Illustrative Drop Path Calculations

Description: Report presenting a wind-tunnel investigation of bomb-release problems by measuring static forces for computation of bomb drop paths. Forces and moments were measured on bombs of three fineness ratios and on a swept-wing fighter-bomber configuration for several positions of the bomb under an open bomb bay. Results regarding contour paths and drop-path calculations are provided.
Date: January 10, 1957
Creator: Smith, Norman F. & Carlson, Harry W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurement of Static Forces on Internally Carried Bombs of Three Fineness Ratios in Flow Field of a Swept-Wing Fighter-Bomber Configuration at a Mach Number of 1.61 With Illustrative Drop-Path Calculations

Description: Report presenting a wind-tunnel investigation of bomb-release problems by measuring static forces for computation of bomb drop paths. Forces and moments were measured on bombs of three fineness ratios and on a swept-wing fighter-bomber airplane for various positions of the bomb under an open bomb bay. The wing of the plane is shown to have a significant effect on the bomb forces before and after the bomb emerged from the bomb bay.
Date: January 10, 1957
Creator: Smith, Norman F. & Carlson, Harry W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressure distribution induced on a flat plate by a supersonic and sonic jet exhaust at a free-stream Mach number of 1.80

Description: Report presenting an experimental investigation of the pressures induced on a flat plate by a propulsive jet exhausting from sonic and supersonic nozzles at a free-stream Mach number of 1.80. Measurements of the pressure distribution on a flat-plate wing were made at zero angle of attack for four different locations of the jet exhaust nozzle beneath the wing. Results regarding the jet-off pressure coefficients, jet-on pressure coefficients, and incremental pressure coefficients are provided.
Date: January 10, 1957
Creator: Leiss, Abraham & Bressette, Walter E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Static longitudinal characteristics at high subsonic speeds of a complete airplane model with a highly tapered wing having the 0.80 chord line unswept and with several tail configurations

Description: Report presenting an investigation at high subsonic speeds of a complete model with a highly tapered wing and several tail configurations. The complete model was tested with a chord-plane tail, a T tail, and a biplane tail. A discussion regarding the pitching-moment characteristics, lift and drag characteristics, and stabilizer characteristics is provided.
Date: January 10, 1957
Creator: Goodson, Kenneth W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Forces and Moments on a Large Ogive-Cylinder Store at Various Locations Below the Fuselage Center Line of a Swept-Wing Bomber Configuration at a Mach Number of 1.61

Description: "A supersonic wind-tunnel investigation on store interference has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.61. Forces and moments were measured on a large ogive-cylinder store in the presence of a 45 degree swept-wing-fuselage bomber configuration for a number of store locations below the fuselage center line. Results of the investigation show that large variations of store lift, drag, and pitch occur with changes in store or airplane angle of… more
Date: January 14, 1957
Creator: Morris, Odell A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Component performance investigation of J71 experimental turbine 7: effect of first-stator adjustment; over-all performance of J71 turbine with 87-percent-design stator area

Description: The performance results, as well as a compressor-turbine match point study based on a particular mode of engine operation, are compared with those previously obtained with the same turbine having first-stator areas 70, 95.6, and 132 percent of design. Maximum efficiencies for all turbine configurations were high, on the order of 87 to 89 percent. The efficiencies obtained at the match points for the 87-, 95.6-, and 132-percent turbines were slightly lower. No match point for the 70-percent turb… more
Date: January 14, 1957
Creator: Schum, Harold J.; Petrash, Donald A. & Davison, Elmer H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Static Aerodynamic Forces and Moments at High Subsonic Speeds on a Canard Missile During Simulated Launching From the Midsemispan Location of a 45 Degree Sweptback Wing-Fuselage-Pylon Combination at Zero Sideslip

Description: Report presenting an investigation at high subsonic speeds to determine the static aerodynamic forces and moments on a canard missile model during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage-pylon combination. Significant variations in all the aerodynamic components were noted with changes in chordwise location of the missile. Results regarding force and moment characteristics and effects of angle of attack and Mach number are provided.
Date: January 14, 1957
Creator: Alford, William J., Jr. & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some experiments at high supersonic speeds on the aerodynamic and boundary-layer transition characteristics of high-drag bodies of revolution

Description: Report presenting measurements made at Mach numbers of 4.0 and 8.3 of the drag, static stability, damping in pitch, and boundary-layer transition characteristics of several high-drag bodies of revolution that might be used for high-speed entry into the earth's atmosphere. The static stability was found to be high with centers of pressure as far aft as 91 percent of the length from the nose. Results regarding the force and moment data, boundary-layer transition, a comparison of roughness height … more
Date: January 14, 1957
Creator: Seiff, Alvin; Sommer, Simon C. & Canning, Thomas N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen