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Experimental Investigation of Flutter and Divergence Characteristics of the Rocket-Motor Fin of the ASROC Missile

Description: Report presenting testing of models of rocket-motor fins of the ASROC missile for flutter and divergence in the supersonic flutter tunnel for a range of Mach numbers. Results indicate that both divergence of the overhung leading edge and flutter occur within the sea-level operating conditions of the missile at Mach numbers above 1.0. Results regarding the flutter boundary, type of flutter encountered, possible solutions to flutter problems, and possible effects of nondestructive type of flutter… more
Date: July 31, 1958
Creator: Levey, Gilbert M. & Hanson, Perry W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental investigation of flutter and divergence characteristics of the rocket-motor fin of the ASROC missile: COORD. No. N-AM-66

Description: Report presenting testing of scale models of rocket-motor fins of the ASROC missile for flutter and divergence in the supersonic flutter tunnel over a range of Mach numbers. Results regarding the flutter boundary, type of flutter encountered, and effects of flutter are provided.
Date: July 31, 1958
Creator: Levey, Gilbert M. & Hanson, Perry W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flutter Investigation on the High Subsonic and Transonic Speed Range on Cantilever Delta-Wing Plan Forms With Leading-Edge Sweepback of 60 Degrees, 53 Degrees 8', and 45 Degrees

Description: Report presenting results of flutter testing on three cantilever delta-wing plan forms at a range of Mach numbers. The time and location of flutter and results of the flutter calculations are provided for each of the wings.
Date: January 31, 1957
Creator: Lauten, William T., Jr. & Burgess, Marvin F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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

Supersonic Free-Flight Measurement of Heat Transfer and Transition on a 10 Degree Cone Having a Low Temperature Ratio

Description: Report presenting an investigation of the heat-transfer coefficients (Stanton number and boundary-layer transition) obtained from a free-flight test of a 10 degree total-angle cone with a 1/16-inch tip radius. Testing occurred over a range of Mach numbers from 1.8 to 3.5 and a range of wall-to-local-stream temperature ratios. Results regarding skin temperatures, heat-transfer coefficient, and boundary-layer transition are presented.
Date: January 31, 1957
Creator: Merlet, Charles F. & Rumsey, Charles B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Combined Effects of Wing Taper and Low Horizontal-Tail Position on Longitudinal Stability of a 45 Degree Sweptback Wing-Body Combination at Transonic Speeds

Description: Report presenting an investigation of the combined effects of wing taper ratio and low horizontal-tail position on the static longitudinal stability of a 45 degree sweptback wing-body combination with an aspect ratio of 4 at a range of Mach numbers. Results regarding tail-off pitch characteristics, tail-on pitch characteristics, and effective flow characteristics over horizontal tail are provided.
Date: October 31, 1956
Creator: Spooner, Stanley H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Increase in Angle of Dead Rise on the Hydrodynamic Qualities of a Seaplane Configuration Incorporating High Wing Loading

Description: Memorandum presenting an investigation to determine the effects of increase in angle of dead rise on the overall hydrodynamic characteristics of a seaplane having a length-beam ratio of 15 and a wing loading of 120 pounds per square foot. In general, increasing the angle of dead rise from 20 to 40 degrees and 60 degrees improved the trim limits of stability and the range of center-of-gravity positions for satisfactory take-off characteristics.
Date: October 31, 1956
Creator: Kapryan, Walter J. & Weinstein, Irving
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An experimental investigation at Mach numbers from 2.1 to 3.0 of circular-internal-contraction inlets with translating centerbodies

Description: Report presenting the total-pressure recovery characteristics of three circular internal-compression inlets with translating centerbodies at a range of free-stream Mach numbers. The inlets differed only in the shape of the internal compression contours. Results regarding the maximum pressure recoveries and pressure-recovery characteristics are provided.
Date: October 31, 1956
Creator: Mossman, Emmett A. & Pfyl, Frank A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Static stability characteristics of a cambered-delta-wing model at high subsonic speeds

Description: Report presenting an investigation at high subsonic speeds to determine the static stability characteristics of a cambered-delta-wing model with wing dihedral angles of 20 degrees and 50 degrees. Results regarding the longitudinal characteristics and lateral characteristics are provided.
Date: October 31, 1956
Creator: Moseley, William C., Jr.
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

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

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
open access

Preflight and flight-test investigation of a 50-percent-magnesium 50-percent JP-4 slurry fuel in a twin engine ram-jet vehicle

Description: Report presenting an investigation conducted by means of preflight and flight tests to determine the performance of a 50-percent-magnesium 50-percent JP-4 slurry fuel in a twin-engine ramjet test vehicle. Data were obtained over a range of Mach numbers. Although a successful flight test was carried out, the performance obtained from preflight testing was below theoretical values.
Date: May 31, 1956
Creator: Trout, Otto F., Jr. & Kennedy, Thomas L.
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

Factors That Affect Operational Reliability of Turbojet Engines

Description: The problem of improving operational reliability of turbojet engines is studied in a series of papers. Failure statistics for this engine are presented, the theory and experimental evidence on how engine failures occur are described, and the methods available for avoiding failure in operation are discussed. The individual papers of the series are Objectives, Failure Statistics, Foreign-Object Damage, Compressor Blades, Combustor Assembly, Nozzle Diaphrams, Turbine Buckets, Turbine Disks, Rollin… more
Date: January 31, 1956
Creator: Lewis Laboratory Staff
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

Interim Report on Free-Spinning-Tunnel Investigation of a 1/25-Scale Model of the McDonnell F3H-1N Airplane, TED No. NACA AD 3100

Description: "An investigation was conducted in the Langley 20-foot free-spinning tunnel on a 1/23-scale model of the McDonnell F3H-1N airplane. The effects of control settings and movements upon the erect and inverted spin and recovery characteristics of the model were determined for the clean condition. Spin-recovery parachute tests were also performed. The results indicated that erect spins obtained on the airplane for the take-off or combat loadings should be satisfactorily terminated if full rudder rev… more
Date: December 31, 1954
Creator: Lee, Henry A. & Wilkes, L. Faye
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
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

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
open access

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

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

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

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
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