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 Serial/Series Title: NACA Research Memorandums
 Collection: National Advisory Committee for Aeronautics Collection
Investigation of Ejection Release Characteristics of Four Dynamically Scaled Internal-Store Shapes from a 1/17-Scale Simulated Bomb Bay of the Republic F-105 Airplane at Mach Numbers of 1.39 and 1.98

Investigation of Ejection Release Characteristics of Four Dynamically Scaled Internal-Store Shapes from a 1/17-Scale Simulated Bomb Bay of the Republic F-105 Airplane at Mach Numbers of 1.39 and 1.98

Date: October 1, 1956
Creator: Lee, J. B.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison and evaluation of two model techniques used in predicting bomb-release motions

Comparison and evaluation of two model techniques used in predicting bomb-release motions

Date: December 27, 1957
Creator: Carlson, H. W.; Geier, D. J. & Lee, J. B.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-Tunnel Flutter Tests at Mach Numbers up to 3.0 of Boeing Wing Models for Weapons System 110A

Wind-Tunnel Flutter Tests at Mach Numbers up to 3.0 of Boeing Wing Models for Weapons System 110A

Date: September 27, 1957
Creator: Levey, G. M.; Rainey, A. G. & Tuovila, W. J.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Static lateral-directional stability characteristics of five contemporary airplane models from wind-tunnel tests at high subsonic and supersonic speeds

Static lateral-directional stability characteristics of five contemporary airplane models from wind-tunnel tests at high subsonic and supersonic speeds

Date: January 4, 1956
Creator: Ball, L. H. & Smith, W. G.
Description: Wind tunnel tests to determine lateral-directional stability of aircraft from transonic to supersonic speeds.
Contributing Partner: UNT Libraries Government Documents Department
Development of a supersonic area rule and an application to the design of a wing-body combination having high lift-to-drag ratios

Development of a supersonic area rule and an application to the design of a wing-body combination having high lift-to-drag ratios

Date: January 1, 1953
Creator: Fischetti, T. L. & Whitcomb, R. T.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Effect of Blunt-Trailing-Edge Modifications on the High-Speed Stability and Control Characteristics of a Swept-Wing Fighter Airplane

The Effect of Blunt-Trailing-Edge Modifications on the High-Speed Stability and Control Characteristics of a Swept-Wing Fighter Airplane

Date: May 26, 1954
Creator: Sadoff, Melvin; Matteson, Frederick H. & Van Dyke, Rudolph D., Jr.
Description: An investigation was conducted on a 35 deg swept-wing fighter airplane to determine the effects of several blunt-trailing-edge modifications to the wing and tail on the high-speed stability and control characteristics and tracking performance. The results indicated significant improvement in the pitch-up characteristics for the blunt-aileron configuration at Mach numbers around 0.90. As a result of increased effectiveness of the blunt-trailing-edge aileron, the roll-off, customarily experienced with the unmodified airplane in wings-level flight between Mach numbers of about 0.9 and 1.0 was eliminated, The results also indicated that the increased effectiveness of the blunt aileron more than offset the large associated aileron hinge moment, resulting in significant improvement in the rolling performance at Mach numbers between 0.85 and 1.0. It appeared from these results that the tracking performance with the blunt-aileron configuration in the pitch-up and buffeting flight region at high Mach numbers was considerably improved over that of the unmodified airplane; however, the tracking errors of 8 to 15 mils were definitely unsatisfactory. A drag increment of about O.OOl5 due to the blunt ailerons was noted at Mach numbers to about 0.85. The drag increment was 0 at Mach numbers above 0.90.
Contributing Partner: UNT Libraries Government Documents Department
Boundary-layer measurements on several porous materials with suction applied

Boundary-layer measurements on several porous materials with suction applied

Date: June 18, 1952
Creator: Mccullough, G. B. & Gambucci, B. J.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Additional experiments with flat-top wing- body combinations at high supersonic speeds

Additional experiments with flat-top wing- body combinations at high supersonic speeds

Date: February 19, 1957
Creator: Gloria, H. R.; Syvertson, C. A. & Wong, T. J.
Description: Flat top wing body configuration effects on aerodynamic characteristics of supersonic aircraft.
Contributing Partner: UNT Libraries Government Documents Department
Performance of JP-4 fuel with fluorine- oxygen mixtures in 1000-pound-thrust rocket engines

Performance of JP-4 fuel with fluorine- oxygen mixtures in 1000-pound-thrust rocket engines

Date: June 11, 1958
Creator: Douglass, H. W. & Nored, D. L.
Description: Fluorine-liquid oxygen mixture and injector design effects on JP-4 jet fuel performance in rocket engines.
Contributing Partner: UNT Libraries Government Documents Department
Analytical studies of the response to longitudinal control of three airplane configurations in landing approaches

Analytical studies of the response to longitudinal control of three airplane configurations in landing approaches

Date: April 9, 1953
Creator: Bihrle, W., Jr. & Stone, R. W., Jr.
Description: Analytical studies of response to longitudinal control of three aircraft configurations in carrier landing approaches.
Contributing Partner: UNT Libraries Government Documents Department