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open access

Analysis of a nuclear-powered ram-jet missile

Description: From Introduction: "The ram-jet missile studied in the present report is one type of shieldless which has the advantage of employing the simplest type of propulsion system."
Date: October 5, 1954
Creator: Rom, Frank E.
open access

Analysis of Rocket, Ramjet, Turbojet Engines for Supersonic Propulsion of Long-Range Missiles 2: Rocket Missile Performance

Description: Memorandum presenting an investigation of the theoretical performance of a two-stage ballistic rocket missile with a centerbody and two parallel boosters for JP4-oxygen and ammonia-fluorine propellants. The missile using the ammonia-fluorine propellant weighs about one-half as much as a missile using JP4-oxygen. Results regarding the optimum missile and effect of variation of design parameters are provided.
Date: October 11, 1954
Creator: Huff, Vearl N. & Kerrebrock, Jack
open access

Analysis of Wind-Tunnel Tests at Low Speeds of a Four-Engine Propeller-Driven Airplane Configuration Having a Wing With 40 Degrees of Sweepback

Description: Report presenting an investigation to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane with a 40 degree swept wing with an aspect ratio of 10. Results regarding components of the lift changes due to operating propellers, components of the pitching-moment changes due to operating propellers, effect of configuration changes on the pitching-moment characteristics of the model, stick-fixed longitudinal stability of the model, reduct… more
Date: October 8, 1954
Creator: Edwards, George G. & Buell, Donald A.
open access

Analytical determination of effect of turbine cooling-air-impeller performance on engine performance and comparison of experimentally determined performance of impellers with and without inducer vanes

Description: Report presenting an analytical and experimental investigation of the effects of cooling-air impeller performance on turbojet-engine performance at 70 and 100 percent of rated engine speed. Analysis indicated that the impeller performance has little effect on engine performance at rated engine speed for the coolant flows considered. Results regarding the impeller total-pressure ratio and cooling air available with compressor bleed are provided.
Date: October 25, 1954
Creator: Schafer, Louis J., Jr. & Hickel, Robert O.
open access

Analytical Study of the Effect of Center-of-Gravity Position on the Response to Longitudinal Control in Landing Approaches of a Swept-Wing Airplane of Low Aspect Ratio Having No Horizontal Tail

Description: Report presenting an investigation of the effect of reducing the static stability by a practical center-of-gravity shift in swept-wing airplanes of low aspect ratio with no horizontal tail. Results regarding relocating the center of gravity, the effect of lift due to elevator deflection, the effect of increased total elevator effectiveness, and the effect of response characteristics over long time periods are provided.
Date: October 15, 1954
Creator: Stone, Ralph W., Jr.
open access

Drag data for 16-inch-diameter ram-jet engine with double-cone inlet in free flight at Mach numbers from 0.7 to 1.8

Description: Report presenting an investigation of air-launched ram jets using models with double-cone inlets with a design free-stream Mach number of 2.4. Drag data are presented in the form of cowl pressure drag, additive drag, internal drag, base drag, and total drag. Mass-flow ratios and ram-jet total-temperature ratios are also provided.
Date: October 25, 1954
Creator: Jones, Merle L.; Rabb, Leonard & Simpkins, Scott H.
open access

Drag Measurements on a 1/6-Scale, Finless, Sting-Mounted NACA RM-10 Missile in Flight at Mach Numbers From 1.1 to 4.04 Showing Some Reynolds Number and Heating Effects

Description: Report discussing a finless NACA RM-10 missile string-mounted on a parent body to determine the total drag, base drag, and wall temperature at peak Mach number 4.04. The total- and base-drag measurements were well-correlated with wind tunnel results and calculations made by using Love's method. The existence of considerable regions of laminar flow on the body during the flight were observed.
Date: October 27, 1954
Creator: Piland, Robert O.
open access

Effect of plug design on performance characteristics of convergent-plug exhaust nozzles

Description: Report presenting an evaluation of the internal performance characteristics of several plug-type nozzles over a range of pressure ratios from 1.5 to 30. Results regarding isentropic plug nozzles, conical plug nozzles, the effect of throat and throat-approach section on performance, and air-flow parameter are provided.
Date: October 25, 1954
Creator: Krull, H. George & Beale, William T.
open access

Effect of rotation of a NACA 1-series E-type cowling on the internal flow and force characteristics of the cowling at Mach numbers up to 0.84 and at an angle of attack of 0 degrees

Description: Report presenting an investigation to determine the effect of rotation on the internal flow and force characteristics of an NACA 1-series E-type cowl, designed to operate with a four-blade single-rotation propeller. Results regarding internal-flow characteristics, force characteristics, and velocity distributions are provided.
Date: October 27, 1954
Creator: Sammonds, Robert I. & Reynolds, Robert M.
open access

The Effect of Wing Profile on the Transonic Characteristics of Rectangular and Triangular Wings Having Aspect Ratios of 3: Transonic Bump Technique

Description: Report presenting an investigation to determine the effect of wing profile on the transonic aerodynamic characteristics of rectangular and triangular wings with aspect ratios of 3. Five wings were compared over a range of Mach and Reynolds number. Results regarding the rectangular and triangular wings and use of transonic area rule are provided.
Date: October 27, 1954
Creator: Nelson, Warren H. & Frank, Joseph L.
open access

Effects of angle of attack and airfoil profile on the two-dimensional flutter derivatives for airfoils oscillating in pitch at high subsonic speeds

Description: Report presenting two-dimensional aerodynamic lift and moment flutter derivatives for moderate and high angles of attack for several airfoil profiles varying in thickness and thickness distribution. The results indicate that the variables angle of attack, airfoil profile, reduced frequency, and Mach number all have significant interdependent effects.
Date: October 15, 1954
Creator: Wyss, John A. & Herrera, Raymond
open access

Effects of Multiaxial Stretching on Crazing and Other Properties of Transparent Plastics

Description: Memorandum presenting an investigation of the effects of orientation by multi-axial stretching on properties of various plastic glazing materials. The materials studied were Lucite HC-222, Plexiglass 55, Gafite, and resin C. Some of the tests conducted included dimensional stability at elevated temperatures, surface abrasion, standard tensile tests, and stress-solvent crazing tests using ethylene dichloride.
Date: October 20, 1954
Creator: Wolock, Irvin & George, Desmond A.
open access

Effects of Secondary-Air Flow on Annular Base Force of a Supersonic Airplane

Description: Memorandum presenting an investigation of the effect of base bleed on the base force of a supersonic-interceptor model in the 8- by 6-foot supersonic wind tunnel. Two groups of fixed-geometry nozzles and shroud combinations simulating double-iris-type configurations were evaluated over a range of secondary to primary exit-diameter ratios.
Date: October 11, 1954
Creator: Vargo, Donald J.
open access

Effects of Secondary-Air Flow on Annular Base Force of a Supersonic Airplane

Description: Memorandum presenting an investigation of the effect of base bleed on the base force of a supersonic-interceptor model in the 8- by 6-foot supersonic wind tunnel. Generally, base pressures greater than ambient were obtained at the engine operating pressure ratios of the primary nozzle.
Date: October 11, 1954
Creator: Vargo, Donald J.
open access

Experimental Determination of Linear Dynamics of Two-Spool Turbojet Engines

Description: Transfer functions descriptive of the response of most engine variables were determined from transient data that were obtained from approximate step inputs in fuel flow and in exhaust-nozzle area. The speed responses of both spools to fuel flow and to turbine-inlet temperature appeared as identical first-order lags. Response to exhaust-nozzle area was characterized by a first-order lag response of the outer-spool speed, accompanied by virtually no change in inner-spool speed.
Date: October 18, 1954
Creator: Novik, David & Heppler, Herbert
open access

Experimental Investigation at High Subsonic Speeds to Determine the Rolling-Stability Derivatives of Three Wing-Fuselage Configurations

Description: Memorandum presenting rolling-stability derivatives for three wing configurations, which were tested on the same fuselage, over a range of Mach numbers and angles of attack. The wings were assorted plan-form configurations of current interest and were not part of a geometrically related series of plan forms. Results regarding basic damping-in-roll results, estimation of rolling derivatives, and estimated effects of Reynolds number are provided.
Date: October 27, 1954
Creator: Sleeman, William C., Jr.
open access

Free-flight measurements of the rolling effectiveness and operating characteristics of a bellows-actuated split-flap aileron on a 60 degree delta wing at Mach numbers between 0.8 and 1.8

Description: Report presenting a free-flight investigation in a range of Mach numbers to determine the maximum deflection, zero-lift rolling effectiveness, and general operating characteristics of a bellows-actuated aileron control system energized by the pitot (impact) pressure. Testing of a system with a partial-span spit-flap aileron on a 60 degree delta wing showed that it is promising for obtaining lateral control at supersonic speeds. Results regarding aileron rolling effectiveness, aileron hinge mome… more
Date: October 18, 1954
Creator: Schult, Eugene D.
open access

Free-flight tests of 45 degree swept wings of aspect ratio 3.15 and taper ratio 0.54 to measure wing damping of the first bending mode and to investigate the possibility of flutter at transonic speeds

Description: Report presenting free-flight tests made on two pairs of wings of aspect ratio 3.15, taper ratio 0.54, and 45 degrees sweepback in the transonic speed range to measure wing damping and to investigate the possibility of flutter. Results regarding the flight test and analysis and discussion are provided.
Date: October 12, 1954
Creator: O'Kelly, Burke R.; Lundstrom, Reginald R. & Lauten, William T., Jr.
open access

Ground Tests of the Elevator Power Control System and Feel Device in a Boeing B-47A Airplane

Description: Memorandum presenting ground tests made on the longitudinal control system in a Boeing B-47A airplane. The simulator tests showed the pilot-airplane-control-system combination to be satisfactory in spite of the relatively large phase lags noticed in the frequency-response tests. Results regarding the relation between elevator angle and stick force, relation between stick angle and stick force, relation between elevator angle and stick angle, and the simulator tests are provided.
Date: October 18, 1954
Creator: Brown, B. Porter
open access

Investigation at supersonic speeds of a translating-spike inlet employing a steep-lip cowl

Description: Report presenting an experimental investigation conducted in the supersonic wind tunnel at three Mach numbers on a translating-spike inlet analytically designed to keep the cone shoulder downstream of the cowl-lip station without a net internal contraction. The inlet in this investigation had an internal cowl-lip angle of 17.5 degrees and was constructed to have the same inlet capture area and maximum cross-sectional area as a previously tested inlet with an internal cowl-lip angle of only 7 de… more
Date: October 11, 1954
Creator: Gorton, Gerald C.
open access

An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Aerodynamic Characteristics of the Configuration Equipped With a Canard Control Surface at a Mach Number of 1.89

Description: Memorandum presenting an investigation conducted in the 4- by 4-foot supersonic pressure tunnel to determine the aerodynamic characteristics of a supersonic aircraft configuration equipped with a canard control surface at a Mach number of 1.89. The model had a 40 degree sweptback tapered wing with an aspect ratio of 4 and 10-percent-thick circular-arc sections normal to the quarter-chord line. Results regarding the pitching-moment characteristics, lift and longitudinal-force characteristics, lo… more
Date: October 18, 1954
Creator: Spearman, M. Leroy & Plazzo, Edward B.
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