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  Partner: UNT Libraries Government Documents Department
 Collection: National Advisory Committee for Aeronautics Collection
Results 13311 - 13320 of 13,806
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Measurement of static forces on externally carried bombs of fineness ratios 7.1 and 10.5 in the flow field of a swept-wing fighter- bomber configuration at a Mach number of 1.6

Measurement of static forces on externally carried bombs of fineness ratios 7.1 and 10.5 in the flow field of a swept-wing fighter- bomber configuration at a Mach number of 1.6

Date: January 31, 1957
Creator: Carlson, H. W. & Geier, D. J.
Description: Static force and interference drag on externally carried bomb in flow field of supersonic, swept wing fighter-bomber aircraft.
Contributing Partner: UNT Libraries Government Documents Department
Transonic flutter investigation of models of the all-movable horizontal tail of a fighter airplane

Transonic flutter investigation of models of the all-movable horizontal tail of a fighter airplane

Date: January 24, 1958
Creator: Sellers, T. B.
Description: Horizontal tail flutter in fighter aircraft at transonic speeds.
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at high subsonic speeds of the effects on static stability characteristics of various modifications to a swept-wing fighter-type airplane model

Wind-tunnel investigation at high subsonic speeds of the effects on static stability characteristics of various modifications to a swept-wing fighter-type airplane model

Date: April 30, 1957
Creator: Goodson, K. W.
Description: Wind tunnel investigations of effect on static stability of modifications to swept wing fighter aircraft model.
Contributing Partner: UNT Libraries Government Documents Department
A Wind-Tunnel Investigation of the Effects of Conical Camber for an Airplane Configuration Having a Triangular Wing of Aspect Ratio 2.2

A Wind-Tunnel Investigation of the Effects of Conical Camber for an Airplane Configuration Having a Triangular Wing of Aspect Ratio 2.2

Date: April 30, 1957
Creator: Boyd, J. W. & Phelps, E. R.
Description: Effects of conical camber for triangular wing- body-tail combinations on aerodynamic characteristics.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of boundary-layer Reynolds number for transition on an NACA 65 sub (215) sup-114 airfoil in the Langley two-dimensional low-turbulence pressure tunnel

Investigation of boundary-layer Reynolds number for transition on an NACA 65 sub (215) sup-114 airfoil in the Langley two-dimensional low-turbulence pressure tunnel

Date: October 1, 1948
Creator: Braslow, A. L. & Visconti, F.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some remarks concerning soaring flight

Some remarks concerning soaring flight

Date: October 1, 1921
Creator: Prandtl, L
Description: The publication of the following details is due to the desire of the editor to have the problems of soaring flight treated on the occasion of the Rhone Soaring Flight Contest.
Contributing Partner: UNT Libraries Government Documents Department
A new dynamometer brake

A new dynamometer brake

Date: September 1, 1921
Creator: Segre, Marco
Description: The mechanism here described belongs to the class of dynamometer brake in which the motive power is transformed into heat in the brake itself. This mechanism was invented by the writer for the purpose of measuring forces in which the two factors, torque and speed, vary within broad limits, the mechanism itself being of simple construction and of still simpler operation.
Contributing Partner: UNT Libraries Government Documents Department
NACA Conference on High-Speed Aerodynamics  A compilation of papers presented

NACA Conference on High-Speed Aerodynamics A compilation of papers presented

Date: January 1, 1958
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Investigation of flow coefficient of circular, square, and elliptical orifices at high pressure ratios

Investigation of flow coefficient of circular, square, and elliptical orifices at high pressure ratios

Date: September 1, 1949
Creator: Callaghan, E. E. & Bowden, D. T.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary Data on Rain Deflection from Aircraft Windshields by Means of High-Velocity Jet-Air Blast

Preliminary Data on Rain Deflection from Aircraft Windshields by Means of High-Velocity Jet-Air Blast

Date: July 25, 1955
Creator: Ruggeri, Robert S.
Description: A preliminary experimental investigation is being conducted to determine the feasibility of preventing rain from impinging on aircraft windshields by means of high-velocity jet-air blast. The results indicate that rain deflection by jet blast appears feasible for flight speeds comparable with landing and take-off speeds of interceptor-type jet aircraft; however, attainment of good visibility through the mist generated by raindrop breakup presents a problem. For the simulated windshield and the lower windshield angles used in the investigation, air-flow rates of the order of 3.3 pounds per minute of unheated air per inch of windshield span were required for adequate rain deflection at a free-stream velocity of 135 miles per hour. A method has been devised whereby it is possible to produce large-diameter water drops (1000 to 1500 p.) in a moving air stream, without breakup, at speeds in excess of 175 miles per hour.
Contributing Partner: UNT Libraries Government Documents Department