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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Tank investigation of the Grumman JRF-5 airplane with a single hydro-ski and an extended afterbody

Tank investigation of the Grumman JRF-5 airplane with a single hydro-ski and an extended afterbody

Date: August 7, 1951
Creator: Ramsen, John A & Gray, George R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tank investigation of the hydrodynamic characteristics of a 1/3.33-scale jet-powered dynamic model of the Martin XP6M-1 flying boat with a revised forebody planing bottom : TED No. NACA DE 385

Tank investigation of the hydrodynamic characteristics of a 1/3.33-scale jet-powered dynamic model of the Martin XP6M-1 flying boat with a revised forebody planing bottom : TED No. NACA DE 385

Date: October 20, 1955
Creator: Blanchard, Ulysse J & Carter, Arthur W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tank investigation of the hydrodynamic characteristics of a 1/13.33-scale jet-powered dynamic model of the Martin XP6M-1 flying boat. : TED No. NACA DE 385

Tank investigation of the hydrodynamic characteristics of a 1/13.33-scale jet-powered dynamic model of the Martin XP6M-1 flying boat. : TED No. NACA DE 385

Date: April 1, 1955
Creator: Carter, Arthur W & Blanchard, Ulysse J
Description: A tank investigation was made of the hydrodynamic characteristics of a 1/13.33-scale jet-powered dynamic model of the 160,000-pound Martin XP6M-1 flying boat. Longitudinal stability during take-off and landing, resistance of the complete model, spray characteristics, flap loads, and effect of sinking speed in smooth and rough water are presented, as well as behavior during taxiing, take-off and landing in rough water. The effect on spray of two bows and several bow-spray-strip modifications and the effect on resistance of afterbody chine strips also are presented.
Contributing Partner: UNT Libraries Government Documents Department
Tank spray tests of a jet-powered model fitted with NACA hydro-skis

Tank spray tests of a jet-powered model fitted with NACA hydro-skis

Date: July 22, 1948
Creator: Wadlin, Kenneth L & Ramsen, John A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tank Tests of 1/5.5-Scale Forward Dynamic Model of the Columbia XJL-1 Amphibian - Langley Tank Model 208, TED No. NACA 2336

Tank Tests of 1/5.5-Scale Forward Dynamic Model of the Columbia XJL-1 Amphibian - Langley Tank Model 208, TED No. NACA 2336

Date: November 13, 1946
Creator: Havens, Robert F.
Description: Tests of a powered dynamic model of the Columbia XJL-1 amphibian were made in Langley tank no.1 to determine the hydrodynamic stability and spray characteristics of the basic hull and to investigate the effects of modifications on these characteristics. Modifications to the forebody chime flare, the step, and the afterbody, and an increase in the angle of incidence of the wing were included in the test program. The seaworthiness and spray characteristics were studied from simulated taxi runs in smooth and rough water. The trim limits of stability, the range of stable positions of the enter of gravity for take-off, and the landing stability were determined in smooth water. The aerodynamic lift, pitching moment, and thrust were determined at speeds up to take-off speed.
Contributing Partner: UNT Libraries Government Documents Department
Tank tests of a 1/5 full-size dynamically similar model of the Army OA-9 amphibian with motor-driven propellers : NACA model 117

Tank tests of a 1/5 full-size dynamically similar model of the Army OA-9 amphibian with motor-driven propellers : NACA model 117

Date: December 1, 1941
Creator: Olson, Roland E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tank Tests of a 1/7-Size Dynamic Model of the Grumman XJR2F-1 Amphibian to Determine the Effect of Slotted- and Split-Type Flaps on Take-Off Stability - NACA Model 212, TED No. NACA 2378

Tank Tests of a 1/7-Size Dynamic Model of the Grumman XJR2F-1 Amphibian to Determine the Effect of Slotted- and Split-Type Flaps on Take-Off Stability - NACA Model 212, TED No. NACA 2378

Date: February 6, 1947
Creator: Land, Norman S. & Zeck, Howard
Description: Additional tests of a 1/7-size model of the Grumman XJR2F-1 amphibian were made in Langley tank no. 1 to compare the behavior during take-off of the model equipped with split- and slotted-type flaps. The slotted flag had a large effect on locating the forward center-of-gravity limits for stable take-offs. Stable take-offs within the normal operating range of positions of the center of gravity could be made with the split flaps deflected 45deg or with the slotted flaps deflected less than 20deg. At flap deflections required for similar take-off stability, the use of split-flaps resulted lower take-off speeds than the use of slotted flaps. An increase in forward acceleration from 1.1 to 4.8 feet per second per second moved the center-of-gravity limit forward approximately 3-percent mean aerodynamic chord.
Contributing Partner: UNT Libraries Government Documents Department
Tank Tests of a 1/7-Size Powered Dynamic Model of the Grumman XJR2F-1 Amphibian: Spray Characteristics, Take-Off and Landing Stability in Smooth Water - Langley Tank Model 212, TED No. NACA 2378

Tank Tests of a 1/7-Size Powered Dynamic Model of the Grumman XJR2F-1 Amphibian: Spray Characteristics, Take-Off and Landing Stability in Smooth Water - Langley Tank Model 212, TED No. NACA 2378

Date: December 4, 1946
Creator: Land, Norman S. & Zeck, Howrad
Description: Tests of a model of the XJR2F-Y amphibian were made in Langley tank no. to determine the spray characteristics and the take-off and landing stability. At a gross load of 22,000 pounds full size, spray entered the propeller disk only at a very narrow range of speeds. The spray striking the flaps was not excessive and no appreciable wetting of the tail surfaces was noted. The trim limits of stability appeared to be satisfactory and the upper-limit porpoising was not violent. The stable range of center-of-gravity locations with flaps set 20deg was well aft of the desired operating range. However, with flaps up, the forward limit was about 18 percent mean aerodynamic chord and the aft limit about 28.5 percent mean aerodynamic chord at a load of 26,000 pounds and with elevators deflected -10deg. Under these conditions the location of the step is considered satisfactory. Tests showed that the effect of water in the nose-wheel well would be to move the forward limit aft about 2-percent mean aerodynamic chord. Without ventilation of the main step, the model skipped during landing at most trims, but this skipping was not violent. With the ventilation, the model skipped lightly only at trims where ...
Contributing Partner: UNT Libraries Government Documents Department
Tank tests of a 1/8-size dynamic model of the PB2Y-3 airplane with increased power : NACA model 131

Tank tests of a 1/8-size dynamic model of the PB2Y-3 airplane with increased power : NACA model 131

Date: June 1, 1943
Creator: Havens, Robert F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Tank Tests of a 1/8-Size Dynamic Model of the PB2Y-3 Airplane with Simulated Jet Motors: NACA Models 131J, 131J-1 and 131J-2

Tank Tests of a 1/8-Size Dynamic Model of the PB2Y-3 Airplane with Simulated Jet Motors: NACA Models 131J, 131J-1 and 131J-2

Date: June 1, 1943
Creator: Havens, Robert F
Description: None
Contributing Partner: UNT Libraries Government Documents Department