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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
Effects of Inlet Modification and Rocket-Rack Extension on the Longitudinal Trim and Low-Lift Drag of the Douglas F5D-1 Airplane as Obtained with a 0.125-Scale Rocket-Boosted Model between Mach Numbers of 0.81 and 1.64, TED No. NACA AD 399

Effects of Inlet Modification and Rocket-Rack Extension on the Longitudinal Trim and Low-Lift Drag of the Douglas F5D-1 Airplane as Obtained with a 0.125-Scale Rocket-Boosted Model between Mach Numbers of 0.81 and 1.64, TED No. NACA AD 399

Date: April 19, 1957
Creator: Hastings, Earl C., Jr. & Dickens, Waldo L.
Description: A flight investigation was conducted to determine the effects of an inlet modification and rocket-rack extension on the longitudinal trim and low-lift drag of the Douglas F5D-1 airplane. The investigation was conducted with a 0.125-scale rocket-boosted model which was flight tested at the Langley Pilotless Aircraft Research Station at Wallops Island, Va. Results indicate that the combined effects of the modified inlet and fully extended rocket racks on the trim lift coefficient and trim angle of attack were small between Mach numbers of 0.94 and 1.57. Between Mach numbers of 1.10 and 1.57 there was an average increase in drag coefficient of about o,005 for the model with modified inlet and extended rocket racks. The change in drag coefficient due to the inlet modification alone is small between Mach numbers of 1.59 and 1.64.
Contributing Partner: UNT Libraries Government Documents Department
Range Performance of Bombers Powered by Turbine-Propeller Power Plants

Range Performance of Bombers Powered by Turbine-Propeller Power Plants

Date: June 20, 1950
Creator: Cline, Charles W.
Description: Calculations have been made to find range? attainable by bombers of gross weights from l40,000 to 300,000 pounds powered by turbine-propeller power plants. Only conventional configurations were considered and emphasis was placed upon using data for structural and aerodynamic characteristics which are typical of modern military airplanes. An effort was made to limit the various parameters invoked in the airplane configuration to practical values. Therefore, extremely high wing loadings, large amounts of sweepback, and very high aspect ratios have not been considered. Power-plant performance was based upon the performance of a typical turbine-propeller engine equipped with propellers designed to maintain high efficiencies at high-subsonic speeds. Results indicated, in general, that the greatest range, for a given gross weight, is obtained by airplanes of high wing loading, unless the higher cruising speeds associated with the high-wing-loading airplanes require-the use of thinner wing sections. Further results showed the effect of cruising at-high speeds, of operation at very high altitudes, and of carrying large bomb loads.
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Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the Grumman XF9F-2 Airplane, TED No. NACA DE 317

Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the Grumman XF9F-2 Airplane, TED No. NACA DE 317

Date: February 4, 1948
Creator: Berman, Theodore
Description: An investigation of the spin and recovery characteristics of a scale model of the Grumman XF9F-2 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model in the flight loading were determined. The investigation also included spin-recovery-parachute, pilot-escape, and rudder-pedal- . force tests. The recovery characteristics of the model were satisfactory for all configurations tested. Spins for the normal control configuration were oscillatory in roll and yaw. Deflecting the leading-edge flaps or the dive brakes did not change the spin and recovery characteristics of the model noticeably. A 10.0-foot tail parachute or a 6.0-foot wing-tip parachute (drag coefficient of 0.75) was found to be effective for recoveries from demonstration spins. The rudder forces in the spin appeared to be within the capabilities of the pilot.
Contributing Partner: UNT Libraries Government Documents Department
Effects of Fuselage Modifications on the Drag Characteristics of a 1/20-Scale Model of the Convair F-102 Airplane at Transonic Speeds

Effects of Fuselage Modifications on the Drag Characteristics of a 1/20-Scale Model of the Convair F-102 Airplane at Transonic Speeds

Date: November 2, 1954
Creator: Kelly, Thomas C. & Osborne, Robert S.
Description: An investigation has been conducted in the Langley 8-foot transonic tunnel to determine the effects of several fuselage modifications on the transonic drag-rise characteristics of a 1/20-scale model of the Convair F-102 airplane. Tests covered an angle-of-attack range from 0deg to about 10deg and a Mach number range from 0.60 to 1.14. Results indicated that the transonic drag rise .for the basic F-102 airplane could be substantially reduced by extending the fuselage after-body approximately 8 percent of the fuselage length. Tests of other bodies indicated that a shorter (4-percent) afterbody extension may have a similar effect on the drag rise. Further improvement of the axial cross-sectional-area distribution of the 8-percent extended configuration through the addition of fuselage volume resulted in additional reductions in the drag rise at a Mach number of 1.0 and caused no or only slight drag penalties at the higher Mach numbers. The results of the present tests generally substantiate the area-rule concept with respect to the prediction of the transonic drag rise through the use of an equivalent-area body of revolution for a practical delta-wing airplane configuration.
Contributing Partner: UNT Libraries Government Documents Department
Ditching Tests of a 1/20-Scale Model of the Northrop B-35 Airplane

Ditching Tests of a 1/20-Scale Model of the Northrop B-35 Airplane

Date: February 22, 1948
Creator: Fisher, Lloyd J.
Description: Tests of a 1/20-scale dynamically similar model of the Northrop B-35 airplane were made to study its ditching characteristics. The model was ditched in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds,and conditions of damage were simulated during the investigation. The ditching characteristics were determined by visual observation and from motion-picture records and time-history acceleration records. Both longitudinal and lateral accelerations were measured. Results are given in tabular form and time-history acceleration curves and sequence photographs are presented. Conclusions based on the model investigation are as follows: 1. The best ditching of the B-35 airplane probably can be made by contacting the water in a near normal landing attitude of about 9 deg with the landing flaps full down so as to have a low horizontal speed. 2. The airplane usually will turn or yaw but the motion will not be violent. The maximum lateral acceleration will be about 2g. 3. If the airplane does not turn or yaw immediately after landing, it probably will trim up and then make a smooth run or porpoise slightly. The maximum longitudinal decelerations that will be encountered are about 6g or 7g. 4. Although the decelerations are not ...
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Tests of the AN/SPS-1 Radar Antenna in the Langley Full-Scale Tunnel

Tests of the AN/SPS-1 Radar Antenna in the Langley Full-Scale Tunnel

Date: January 1, 1948
Creator: May, Ralph W., Jr.
Description: Tests have been conducted to determine the drive-motor torque and the static force and moment characteristics of the AN/SPS-1 radar antenna. Shifting the longitudinal position of the antenna had very little effect on the drive-motor torque, which reached a maximum value expressed in terms of dynamic pressure (T/q)(sub max) of 1.15 at an azimuth angle of 245 deg. The maximum observed values of rolling, pitching, and yawing moments in terms of dynamic pressure are -29.0, 66.6, and 13.4, respectively.
Contributing Partner: UNT Libraries Government Documents Department
Flight Measurements of Lateral and Directional Stability and Control Characteristics of the Grumman F8F-1 Airplane

Flight Measurements of Lateral and Directional Stability and Control Characteristics of the Grumman F8F-1 Airplane

Date: January 1, 1945
Creator: Crane, H. L. & Reeder, J. P.
Description: This paper presents the results of flight tests to determine the lateral and directional stability and control characteristics of the Grumman F8F-1 airplane with three vertical-tail configurations. The data presented herein have no bearing on the performance characteristics of the airplane, which were not measured but which were considered to be exceptionally good. The conclusions reached regarding the lateral and directional stability and control characteristics may be summarized as follows: 1. It was found that the directional stability was poor with the production vertical tail. Addition of a 12-inch extension to the vertical fin and rudder produced a desirable improvement in directional stability and control characteristics. However, further enlargement of the vertical tail would be required to make the directional stability satisfactory in all respects. 2. There was a tendency for the rudder control force to overbalance at large angles of right sideslip with the modified vertical tails. There was no such tendency with the production tail configuration which included a dorsal fin. It was concluded that the dorsal fin should have been retained on the modified vertical tails. 3. The aileron control characteristics were better than those of many comparable airplanes which have been tested. However, the ailerons did ...
Contributing Partner: UNT Libraries Government Documents Department
Investigation of effects of movable exhaust-nozzle plug on operational performance of 20-inch ram jet

Investigation of effects of movable exhaust-nozzle plug on operational performance of 20-inch ram jet

Date: July 27, 1948
Creator: Sterbentz, William H & Wilcox, Fred A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation of horizontal tails II : unswept and 35 degree swept-back plan forms of aspect ratio 4.5

Wind-tunnel investigation of horizontal tails II : unswept and 35 degree swept-back plan forms of aspect ratio 4.5

Date: June 3, 1948
Creator: Dods, Jules B , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Incipient spin characteristics of a 1/25-scale model of the Chance Vought XF8U-1 airplane : TED No. NACA AD 3118

Incipient spin characteristics of a 1/25-scale model of the Chance Vought XF8U-1 airplane : TED No. NACA AD 3118

Date: April 17, 1958
Creator: Healy, Frederick M
Description: None
Contributing Partner: UNT Libraries Government Documents Department