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Flight Measurements of the Rudder Control and Sideslip Characteristics of Four Vertical Tail Arrangements on the P-40 Series Airplanes

Description: Report presenting an investigation of rudder trim force change with speed and power, rudder force reversals in sideslips, and rudder positions in sideslips and straight flight of a P-40E airplane. Quantitative measurements of the items were made on three other vertical arrangements.
Date: October 1942
Creator: Johnson, Harold I. & Vensel, Joseph R.
Partner: UNT Libraries Government Documents Department

Altitude Wind Tunnel Investigation of the Prototype J40-WE-8 Turbojet Engine Without Afterburner

Description: From Introduction: "As part of a comprehensive investigation of the J40 turbojet engine conducted at the NACA Lewis altitude wind tunnel, the steady-state engine performance of the prototype J40-WE-8 turbojet engine without afterburner was obtained and is presented herein. A basic redesign of the compressor and other modifications in the compressor and the combustor were incorporated in the XJ40-WE-6 turbojet engine (references 2 and 3). In this report the modified engine is designated "the prototype J40-WE-8 without afterburner."
Date: August 6, 1953
Creator: McAulay, John E. & Kaufman, Harold R.
Partner: UNT Libraries Government Documents Department

Effect of rotor- and stator-blade modifications on surge performance of an 11-stage axial-flow compressor 2: redesigned compressor for XJ-40-WE-6 engine

Description: Report presenting an investigation to increase the compressor surge-limit pressure ratio of the XJ40-WE-6 turbojet engine at high equivalent speeds. An evaluation of the basic redesign of the compressor and 11 additional modifications are examined.
Date: May 25, 1953
Creator: Conrad, E. William; Finger, Harold B. & Essig, Robert H.
Partner: UNT Libraries Government Documents Department

Effect of rotor-and stator-blade modifications on surge performance of an 11-stage axial-flow compressor 1: original production compressor of XJ40-WE-6 engine

Description: Report presenting an investigation to increase the compressor surge-limit pressure ratio of the XJ40-WE-6 turbojet engine at high equivalent speeds. The two compressor modifications investigated included twisting rotor blades to change blade section angles and inserting new stator diaphragms with different blade angles. Results regarding the effect of surge limit on engine performance, performance map of original compressor with mixer, effect of blade modifications on surge line, effect of mixer on surge limit, and effect of compressor modifications on performance are provided.
Date: May 20, 1953
Creator: Finger, Harold B.; Essig, Robert H. & Conrad, E. William
Partner: UNT Libraries Government Documents Department

Altitude operational characteristics of prototype J40-WE-8 turbojet engine

Description: From Introduction: "The altitude performance characteristics of the prototype J40-WE-8 turbojet engine were determined in the NACA Lewis altitude wind tunnel. The altitude operational characteristics of the engine are presented herein. The results of a brief study of the effect of the two different grades of fuel (MIL-F-5624A grades JP-3 and JP-4) on steady-state engine performance at an altitude of 45,000 feet and a flight Mach number of 0.20 are also given."
Date: August 14, 1953
Creator: Sobolewski, Adam E. & Lubick, Robert J.
Partner: UNT Libraries Government Documents Department

Performance of a 13-Stage Development Compressor for the J40-WE-24 Engine at Equivalent Speeds from 30 to 112 Percent of Design

Description: The performance of a 13-stage development compressor for the J40-WE-24 engine has been determined at equivalent speeds from 30 to 112 percent of design. The design total-pressure ratio of 6.0 and the design weight flow of 164 pounds per second were not attained, An analysis was conducted to determine the reasons for the poor performance at the design and over-design speed. The analysis indicated that most of the difficulty could be attributed to the fact that the first stage was overcompromised to favor part-speed performance,.
Date: April 9, 1953
Creator: Hatch, James E.; Lucas, James G. & Finger, Harold B.
Partner: UNT Libraries Government Documents Department

Performance of Air-Launched T-40 Rocket Motors with Two Types of Igniter

Description: Air-launched firings of eight T-40 rockets have been made. An average total impulse of 22,870 pound-seconds was observed for four of the rounds mounted in cone-cylinder vehicles. Maximum velocities of over 5000 feet per second were observed for two of the rounds with approximately 70-pound pay loads.
Date: October 25, 1954
Creator: Disher, J. H.
Partner: UNT Libraries Government Documents Department

Some Effects of Propeller Operation on the Distribution of the Load on the Vertical Tail Surface of a Typical Pursuit Airplane

Description: Report discusses the results of testing on the pressure distribution at several longitudinal sections of the vertical tail surface of the Curtiss P-40K airplane at various angles of attack and angles of yaw and with the propeller removed and propeller operating. Results regarding the chordwise pressure distributions, effects of propeller operation on the spanwise distribution of normal-force coefficient, total normal-force coefficients, and effect of propeller operation on the variation of vertical-tail normal-force coefficients are presented.
Date: March 1944
Creator: Sweberg, Harold H. & Dingeldein, Richard C.
Partner: UNT Libraries Government Documents Department

Some Flight Measurements on Pressure Distribution During Tail Buffeting

Description: Report presenting pressure-distribution measurements obtained from the horizontal tail surfaces of the Curtiss P-40K airplane during low-speed pull-ups to abrupt stall in which tail buffeting was experienced. The chordwise load distributions during buffeting are similar to those experienced during angle-of-attack changes. The location of the stall and frequency of stall disturbances are also described.
Date: October 1945
Creator: Boshar, John
Partner: UNT Libraries Government Documents Department

Vibration Surveys of the P-40 Rudder and Fin-Rudder Assembly

Description: "The following surveys on the vibration response of the P-40 rudder and fin-rudder assembly were conducted during the fall of 1942 for the purpose of obtaining information on the flutter characteristics of high-speed airplanes of known performance. The tests on the rudder alone were made with the rudder suspended in a floating condition; the tests on the fin-rudder unit were made with the fin rigidly fastened to a concrete base" (p. 1). A variety of figures and diagrams for the assembly are provided.
Date: April 1943
Creator: Theodorsen, Theodore & Regier, Arthur A.
Partner: UNT Libraries Government Documents Department

Altitude Investigation of Several Afterburner Configurations for the J40-WE-8 Turbojet Engine

Description: "An investigation was conducted in the Lewis altitude wind tunnel to evaluate the performance and operational characteristics of the J40-WE-8 afterburner. A brief program of minor modifications to the flame holder, diffuser, and fuel system was undertaken to improve at a burner-inlet pressure level of 620 pounds per square foot. At this pressure level, modifications to the fuel system resulted in an increase in maximum net thrust from 1500 to 1600 pounds and a reduction in specific fuel consumption in the stoichiometric region from 3.70 to 3.15 pounds of fuel per hour per pound of net thrust" (p. 1).
Date: July 16, 1953
Creator: Conrad, E. William & Campbell, Carl E.
Partner: UNT Libraries Government Documents Department

Measurement of Individual Aileron Hinge Moments and Aileron Control Characteristics of a P-40F Airplane

Description: "Flight measurements have been made of the individual aileron hinge moments, aileron rolling effectiveness pb/2V ,and stick-force characteristics in abrupt aileron rolls with a P-40F airplane (AAF No. 41-14119) over an indicated airspeed range from 108 to 304 miles per hour. Three methods for measuring the rate of change of hinge moment with angle of attack were investigated. Presented for comparison with the flight results are data from two-dimensional wind-tunnel tests of the wing-aileron profile as measured at the center aileron hinge" (p. 1).
Date: January 29, 1945
Creator: Goranson, R. Fabian
Partner: UNT Libraries Government Documents Department

Investigation of the I-40 Jet-Propulsion Engine in the Cleveland Altitude Wind Tunnel 1: Performance and Windmilling Drag Characteristics

Description: Report presenting the performance characteristics of the I-40 jet-propulsion engine for a range of altitudes and ram pressure ratios. Results regarding component efficiencies, engine performance, generalizing factors, and windmilling drag characteristics are provided.
Date: August 24, 1948
Creator: Gendler, Stanley L. & Koffel, William K.
Partner: UNT Libraries Government Documents Department

A complete tank test of the hull of the Sikorsky S-40 flying boat - American Clipper Class

Description: The results of a complete test in the N.A.C.A. tank on a model of the hull of Sikorsky S-40 flying boat ('American Clipper') are reported. The test data are given in tables and curves. From these data non-dimensional coefficients are derived for use in take-off calculations and the take-off time and run for the S-40 are computed. The computed take-off time was obtained by the Sikorsky Aviation Corporation in performance tests of the actual craft.
Date: December 1934
Creator: Dawson, John R.
Partner: UNT Libraries Government Documents Department

The S.P.C.A. 40 T Commercial Airplane (French): An All-Metal Cantilever Monoplane

Description: Circular describing the S.P.C.A. 40 T, which is a commercial all-metal cantilever airplane that was guided by the two essential requirements of economy and safety in its design. Details of the design, power, test results, fuel tanks, characteristics, performances, drawings, and photographs are provided.
Date: April 1931
Partner: UNT Libraries Government Documents Department