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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.
Partner: UNT Libraries Government Documents Department

Preliminary empirical design requirements for the prevention of tumbling of airplanes having no horizontal tails

Description: Report presenting an investigation of the design characteristics and loadings conducive to the tumbling of airplanes with no horizontal tails. Empirical design requirements based on model testings of 18 different configurations and an explanation of the phenomena of tumbling are provided.
Date: October 11, 1950
Creator: Bryant, Robert L.
Partner: UNT Libraries Government Documents Department

Model ditching investigations of three airplanes equipped with hydro-skis

Description: Report presenting an investigation to determine the ditching characteristics of three typical multiengine airplanes equipped with different arrangements of hydro-ski ditching gear. The behavior was determined from visual observations, acceleration records, and motion pictures of the landings. Results regarding ski size, shape, and location are provided.
Date: April 25, 1950
Creator: Fisher, Lloyd J.
Partner: UNT Libraries Government Documents Department

Flight measurements of base pressure on bodies of revolution with and without simulated rocket chambers

Description: Report presenting base pressures measured in flight on fin-stabilized bodies of revolution with and without rocket chambers and a converging afterbody at a range of Mach numbers. Pressures were found to be higher over the center portion of the bases of models with rocket chambers than edge pressures, while center base pressures on models without rocket chambers were lower than edge pressures.
Date: November 16, 1950
Creator: Peck, Robert F.
Partner: UNT Libraries Government Documents Department

Investigation of the NACA 3-(3)(05)-05 eight-blade dual-rotating propeller at forward Mach numbers to 0.925

Description: Report presenting force testing on an NACA 3-(3)(05)-05 eight-blade dual-rotating propeller at a range of blade angles. Results indicated that good efficiencies can be obtained at high subsonic forward Mach numbers by operation at high blade angle. Results regarding the propeller characteristics, individual power coefficients, effect of forward Mach number on the maximum efficiency of the dual propeller, and effect of small changes in the rear-propeller blade angle on the dual-propeller characteristics are also provided.
Date: June 19, 1950
Creator: Platt, Robert J., Jr. & Shumaker, Robert A.
Partner: UNT Libraries Government Documents Department

Investigation of the NACA 4-(4)(06)-057-45A and NACA 4-(4)(06)-57-45B two-blade swept propellers at forward Mach numbers to 0.925

Description: Report presenting an investigation of the NACA 4-(4)(06)-057-45A and NACA 4-(4)(06)-057-45B two-blade swept propellers in the high-speed tunnel at blade angles of 25 degrees, 55 degrees, 60 degrees, 65 degrees, and 70 degrees. The swept propellers were compared with straight propellers and were found to be 10 percent more efficient at a forward Mach number of 0.85 for the design blade angle of 60 degrees. Results regarding the effect of forward Mach number, blade sweep, advance ratio, and constant power coefficient on efficiency are also provided.
Date: February 6, 1950
Creator: Delano, James B. & Harrison, Daniel E.
Partner: UNT Libraries Government Documents Department

Damping in roll of rectangular wings of several aspect ratios and NACA 65A-series airfoil sections of several thickness ratios at transonic and supersonic speeds as determined with rocket-powered models

Description: Report presenting rocket-powered flight tests to determine the damping in roll of rectangular wings of various aspect ratios and thickness ratios using NACA airfoil sections. The experimental damping in roll was consistently lower than what was predicted theoretically.
Date: August 24, 1950
Creator: Edmondson, James L.
Partner: UNT Libraries Government Documents Department

Wind-tunnel tests of a 0.16-scale model of the X-3 airplane at high subsonic speeds : additional stability and control characteristics and the aerodynamic effects of external stores and ram jets

Description: Report presenting additional wind-tunnel tests of a model of the X-3 airplane at low and high subsonic numbers to investigate the lateral and longitudinal-stability and control characteristics. Results regarding the aerodynamic characteristics in pitch and aerodynamic characteristics in yaw are provided.
Date: June 13, 1950
Creator: Cleary, Joseph W. & Mellenthin, Jack A.
Partner: UNT Libraries Government Documents Department

Wind-tunnel tests of a 0.16-scale model of the X-3 airplane at high subsonic speeds: stability and control characteristics

Description: Report presenting static lateral- and longitudinal-stability tests of a scale model of a projected, low-aspect-ratio, supersonic airplane at low and high subsonic Mach numbers. The wing was equipped with leading-edge flaps and had a modified double-wedge airfoil with sharp leading and trailing edges. Results regarding lift characteristics, static longitudinal stability and control, lateral and directional stability, drag characteristics, and wing and fuselage tuft studies are provided.
Date: April 21, 1950
Creator: Hamilton, William T. & Cleary, Joseph W.
Partner: UNT Libraries Government Documents Department

Low-speed tests of a model simulating the phenomenon of control-surface buzz

Description: Report presenting low-speed tests of an airfoil model with a freely hinged flap attached to spoilers which passed through slots in the airfoil ahead of the hinge line. Testing indicated that buzz is not caused simply by buffeting of a flap by separated flow. Results regarding the oscillations experienced with the spoiler and flap in several positions are provided.
Date: August 16, 1950
Creator: Phillips, William H. & Adams, James J.
Partner: UNT Libraries Government Documents Department

Positioning investigation of single slotted flaps on a 47.7 degrees sweptback wing at Reynolds numbers of 4.0 x 10(exp 6) and 6.0 x 10(exp 6)

Description: Report presenting a low-speed wind tunnel investigation to determine the relationship between the flap effectiveness and the horizontal and vertical position of a partial-span single slotted flap on a sweptback wing-fuselage combination. Results regarding maximum lift, lift increment, and pitching moment are provided.
Date: October 9, 1950
Creator: Spooner, Stanley H. & Mollenberg, Ernst F.
Partner: UNT Libraries Government Documents Department

Stall Characteristics Obtained from Flight 10 of Northrop X-4 No. 2 Airplane (USAF No. 46-677)

Description: NACA instrumentation has been installed in the X-4 airplanes to obtain stability and control data during the acceptance tests conducted by the Northrop Aircraft Corporation. This report presents data obtained on the stalling characteristics of the airplane in the clean and gear- down configurations. The center of gravity was located at approximately 18 percent of the mean aerodynamic chord during the tests. The results indicated that the airplane was not completely stalled when stall was gradually approached during nominally U accelerated flight but that it was completely stalled during a more abruptly approached stall in accelerated flight. The stall in accelerated flight was relatively mild, and this was attributed to the nature of the variation of lift with angle of attack for the 001-614 airfoil section, the plan form of the wing, and to the fact that the initial sideslip at the stall produced (as shown by wind-tunnel tests of a model of the airplane) a more symmetrical stall pattern.
Date: February 27, 1950
Creator: Sadoff, Melvin & Sisk, Thomas R.
Partner: UNT Libraries Government Documents Department

Analytical and experimental investigation of thrust augmentation of axial- and centrifugal-compressor turbojet engines by injection of water and alcohol in combustion chambers

Description: Report presenting an investigation of thrust augmentation by injection of water and water-alcohol mixtures in the combustion chambers at sea-level zero-ram flight conditions on 4000-pound-thrust axial-flow and centrifugal-flow turbojet engines. Thrust augmentation, compressor characteristics, fuel flow, and turbine-outlet-temperature distributions are presented for various injection rates and water-alcohol mixtures.
Date: April 13, 1950
Creator: Gabriel, David S.; Dowman, Harry W. & Jones, William L.
Partner: UNT Libraries Government Documents Department

Low-Speed Investigation of a 0.16-Scale Model of the X-3 Airplane: Longitudinal Characteristics

Description: Report presenting a wind-tunnel investigation of the low-speed static longitudinal characteristics of a model of the X-3 airplane with the wing flaps neutral and deflected. Results regarding those characteristics with the flaps neutral, with the flaps fully deflected, in the presence of a ground plane, with the flaps partially deflected, and effect of miscellaneous changes of the model are provided.
Date: September 8, 1950
Creator: Delany, Noel K. & Hayter, Nora-Lee F.
Partner: UNT Libraries Government Documents Department

The External-Shock Drag of Supersonic Inlets Having Subsonic Entrance Flow

Description: Memorandum presenting a determination of the external-shock drags of supersonic inlets with circular cross sections from shadow photographs at a Mach number of 2.70 for a low-external-compression and a high-external-compression inlet. The calculated mass flow for both types of inlets showed reasonably good agreement with the measured values. Results as determined by the characteristics method and the approximate method are provided.
Date: December 20, 1950
Creator: Nucci, Louis M.
Partner: UNT Libraries Government Documents Department

Large-Scale Flight Measurements of Zero-Lift Drag at Mach Numbers from 0.90 to 1.95 of 1/14-Scale Model of the Northrop MX-775B Pilotless Aircraft with Small Body

Description: A flight test was made a t high subsonic, transonic, and supersonic speeds and at high Reynolds numbers to determine the zero-lift drag of a 1/14-scale model of the Northrop MX-775B pilotless aircraft with small small body. The triangular wing of the model had 67.5 deg leading-edge sweep and 15 deg. trailing-edge sweep, The wing airfoil sections were modified NACA 0004 sections. The drag coefficient based on total wing area was 0.0107 at Mach number 1.60. At transonic speeds the maximum drag coefficient was 0.0125. The force-break Mach number was 0,98.
Date: August 17, 1950
Creator: Gillespie, Warren, Jr. & Arbic, Richard G.
Partner: UNT Libraries Government Documents Department

Performance of J33-A-27 Turbojet-Engine Compressor, III, Over-All Performance Characteristics of Modified Compressor with Water Injection at Design Equivalent Speed of 11,800 RPM

Description: An investigation was conducted to determine the effects of water injection on the over-all performance of a modified J33-A-27 turbojet-engine compressor at the design equivalent speed of 11,800 rpm. The water-air ratio by weight was 0.05. With water injection the peak pressure ratio increased 9.0 per- cent, the maximum efficiency decreased 15 percent (actual numerical difference 0.12), and. the maximum total weight flow increased 9.3 percent.
Date: June 9, 1950
Creator: Withee, Joseph R., Jr.; Beede, William L. & Ginsburg, Ambrose
Partner: UNT Libraries Government Documents Department

Effect of an Autopilot Sensitive to Yawing Velocity on the Lateral Stability of the Douglas D-558-II Airplane

Description: A theoretical investigation has been made to determine the effect on the lateral stability of the Douglas D-58-II airplane of an autopilot sensitive to yawing velocity. The effects of inclination of the gyro spin axis to the flight path and of tire lag in the autopilot were also determined. The flight conditions investigated included landing at sea level, approach condition at 12,000 feet, and cruising at 50,000 feet at Mach numbers of 0.80 and 1.2. The results of the investigation indicated that the lateral stability characteristics of the D-558-II airplane for the flight condition discussed should satisfy the Air Force - Navy period-damping criterion when the proposed autopilot is installed. Airplane motions in sideslip subsequent to a disturbance in sideslip are presented for several representative flight conditions in which a time lag in the autopilot of 0.10 second was assumed.
Date: August 17, 1950
Creator: Gates, Ordway B., Jr. & Sternfield, Leonard
Partner: UNT Libraries Government Documents Department

Results of the Flight Test of a Dummy of the MX-656 Rocket-Propelled Models

Description: The data obtained from the flight of a simplified (dummy) rocket-propelled model of the MX-656 have been analyzed to determine the booster-model characteristics and the model-alone characteristics up to a Mach number of 1.3. The data indicate that the model-booster combination is satisfactory. The model alone is longitudinally stable i n the Mach number range covered by the test (0.9 to 1.3) with the center of gravity at -15 percent of the mean aerodynamic chord. With the stabilizer setting at 0 deg. the variation of normal-force coefficient with Mach number is not large. The total-drag-coefficient variation with Mach number is not unusual. About 12 percent of the total drag at a Mach number of 1.3 can be attributed to body base drag.
Date: January 12, 1950
Creator: Mitchell, Jesse L. & Peck, Robert F.
Partner: UNT Libraries Government Documents Department

Preliminary Results of a Flight Investigation of 1/6-Scale Rocket-Powered Models of the Bell MX-776 to Determine Aileron Rolling Effectiveness and Total Drag

Description: An experimental investigation of the variation of aileron rolling effectiveness and total drag with Mach number has been made using 1/6-scale rocket-propelled models of the Bell MX-776. Three models having constant-chordwise-thickness full-span aileron at approximate deflections of 2 deg, 5 deg, and 15 deg have been flown. Positive control effectiveness over the Mach number range between approximately 0.5 and 1.2 was obtained from the models and no indication of reversal of effectiveness was encountered. The ratio of tip helix angle to aileron deflection indicated a decrease in proportional rolling effectiveness with increasing deflections in the Mach number range from approximately 0.7 to 1.0. A drag rise of about 125 percent in the transonic region between Mach numbers of 0.85 and 1.02 followed by a gradual decrease at higher speeds was revealed.
Date: January 1, 1950
Creator: Stevens, Joseph E.
Partner: UNT Libraries Government Documents Department

Ditching Investigation of a 1/14-Scale Model of the Northrop C-125 Airplane

Description: An investigation of a 1/14-scale dynamically similar model of the Northrop C-125 airplane was made to determine the ditching characteristics and proper ditching technique for the airplane. Various conditions of damage, landing attitude, flap setting, and speed were investigated. The behavior of the model was determined from visual observations, motion-picture records, and time-history deceleration records. The results of the investigation are presented in table form, photographs, and curves. It was concluded that the airplane should be ditched at a nose-high landing attitude (near 8 deg) with flaps full down. The fixed landing gear will cause the airplane to dive. The fuselage will be damaged and will probably flood rapidly. Longitudinal decelerations will be about 4g and the length of landing run will be about two fuselage lengths. If the main landing gear could be jettisonable or retractable the ditching characteristics would be greatly improved.
Date: 1950
Creator: Fisher, Lloyd J. & Windham, John O.
Partner: UNT Libraries Government Documents Department

Free-Spinning-Tunnel Investigation of a 1/24-Scale Model of the Grumman AF-2S, -2W Airplane

Description: An investigation of the spin and recovery characteristics of a 1/24-scale model of the Grumman AF-2S, -2W airplane was conducted in the Langley 20-foot free-spinning tunnel. The effects of controls on the erect and inverted spin and recovery characteristics for a range of possible loadings of the.airplane were determined. The effect of a revised-tail installation (small dual fins added to the stabilizer of the original tail and the vertical-tail height of the original tail increased) and the effect of various ventral-fin and antispin-fillet installations were determined. The investigation also included spin-recovery parachute tests.
Date: March 12, 1950
Creator: Klinar, Walter J. & Wilson, Jack H.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of a Full-Scale Model of the Hughes MX-904 Missile

Description: A wind-tunnel investigation has been conducted to determine the stability and control characteristics of a full-size model of the Hughes MX-904 missile. Aerodynamic characteristics of the complete model through moderate ranges of angles of attack and yaw, with an additional test made through an angle of attack of 180 degrees, are presented. The effects of horizontal tail deflection are also included.
Date: January 1, 1950
Partner: UNT Libraries Government Documents Department

Investigation of the Spin and Recovery Characteristics of a 0.057-Scale Model of the Modified Chance Vought XF7U-1 Airplane. TED No. NACA DE 311

Description: An investigation has been conducted in the Langley 20-foot free-spinning tunnel to determine the spin and recovery characteristics of a 0.057-scale model of the modified Chance Vought XF7U-1 airplane. The primary change in the design from that previously tested was a revision of the twin vertical tails. Tests were also made to determine the effect of installation of external wing tanks. The results indicated that the revision in the vertical tails did not greatly alter the spin and recovery characteristics of the model and recovery by normal use of controls (fill rapid rudder reversal followed approximately one-half turn later by movement of the stick forward of neutral) was satisfactory. Adding the external wing tanks to cause the recovery characteristics to become critical and border on an unsatisfactory condition; however, it was shown that satisfactory recovery could be obtained by jettisoning the tanks, followed by normal recovery technique.
Date: May 29, 1950
Creator: Berman, Theodore & Pumphrey, Norman E.
Partner: UNT Libraries Government Documents Department