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Correlations Among Ice Measurements, Impingement Rates Icing Conditions, and Drag Coefficients for Unswept NACA 65A004 Airfoil

Correlations Among Ice Measurements, Impingement Rates Icing Conditions, and Drag Coefficients for Unswept NACA 65A004 Airfoil

Date: February 1, 1958
Creator: Gray, Vernon H.
Description: An empirical relation has been obtained by which the change in drag coefficient caused by ice formations on an unswept NACA 65AO04 airfoil section can be determined from the following icing and operating conditions: icing time, airspeed, air total temperature, liquid-water content, cloud droplet impingement efficiencies, airfoil chord length, and angles of attack. The correlation was obtained by use of measured ice heights and ice angles. These measurements were obtained from a variety of ice formations, which were carefully photographed, cross-sectioned, and weighed. Ice weights increased at a constant rate with icing time in a rime icing condition and at progressively increasing rates in glaze icing conditions. Initial rates of ice collection agreed reasonably well with values predicted from droplet impingement data. Experimental droplet impingement rates obtained on this airfoil section agreed with previous theoretical calculations for angles of attack of 40 or less. Disagreement at higher angles of attack was attributed to flow separation from the upper surface of the experimental airfoil model.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of Aerodynamic and Icing Characteristics of Recessed Fuel-Vent Configurations

Investigation of Aerodynamic and Icing Characteristics of Recessed Fuel-Vent Configurations

Date: March 1, 1949
Creator: Ruggeri, Robert S.; VonGlahn, Uwe H. & Rollins, Vern G.
Description: An investigation has been conducted in the NACA Cleveland icing research tunnel to determine the aerodynamic and icing characteristics of several recessed fuel-vent configurations. The vents were investigated aerodynamically to obtain vent-tube pressures and pressure distributions on the ramp surface as functions of tunnel-air velocity and angle of attack. Icing investigations were made to determine the vent-tube pressure losses for several icing conditions at tunnel-air velocities ranging from 220 to 440 feet per second. In general, under nonicing conditions, the configurations with diverging ramp walls maintained, vent-tube pressures greater than the required marginal value of 2 inches of water positive pressure differential between the fuel cell and the compartment containing the fuel cell for a range of angles of attack from 0 to 14deg at a tunnel-air velocity of approximately 240 feet per second. A configuration haying divergIng ramp sldewalls, a 7deg ramp angle; and vent tubes manifold,ed to a common plenum chamber opening through a slot In the ramp floor gave the greatest vent-tube pressures for all the configurations investigated. The use of the plenum chamber resulted in uniform pressures in all vent tubes. In a cloud-icing condition, roughness caused by ice formations on the airfoil surface ahead of ...
Contributing Partner: UNT Libraries Government Documents Department
Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing Model of the Northrop MX-775A Missile with Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail

Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing Model of the Northrop MX-775A Missile with Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail

Date: February 11, 1955
Creator: Arbic, R. G.
Description: Results are presented of a free-flight investigation between Mach numbers of 0.7 to 1.3 and Reynolds numbers of 3.1 x 10(exp 6) to 7.0 x 10(exp 6) to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. This missile has a weng, body, and vertical tail, but has no horizontal tail. The basic wing plan form has an aspect ratio of 5.5, 45 deg of sweepback of the 0.406 streamwise chord line, and a taper ratio of 0.4. A 1/10-scale steel-wing model of the missile was flown with modifications to the basic wing plan form consisting of leading-edge chord-extensions deflected 7 deg downward together with the forward 15 percent of the wing chord, and inboard trailing-edge flaps deflected 5 deg downward. In addition, the model had a static-pressure tube mounted at the tip of the vertical tail for position-error measurements and had a speed brake also mounted on the vertical tail to trim the model to positive lift coefficients and to permit determination of the trim and drag effectiveness of the brake. The data are uncorrected for the effects of wing elasticity, but experimental wing influence coefficients are presented.
Contributing Partner: UNT Libraries Government Documents Department
Supersonic Investigation of the Lift, Drag, Static Stability, and Hinge-Moment Characteristics of a Rocket-Powered Model of a Ballistic-Missile Configuration

Supersonic Investigation of the Lift, Drag, Static Stability, and Hinge-Moment Characteristics of a Rocket-Powered Model of a Ballistic-Missile Configuration

Date: September 28, 1956
Creator: Gillespie, W., Jr.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-flight investigation of the full-scale Hughes Falcon missile, D configuration, to determine aileron effectiveness and damping in roll

Free-flight investigation of the full-scale Hughes Falcon missile, D configuration, to determine aileron effectiveness and damping in roll

Date: November 19, 1954
Creator: Lundstrom, R. R.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight Investigation of a Roll-Stabilized Ramjet Test Vehicle over a Mach Number Range of 2.3 to 2.7

Flight Investigation of a Roll-Stabilized Ramjet Test Vehicle over a Mach Number Range of 2.3 to 2.7

Date: October 7, 1955
Creator: Kennedy, T. L. & Trout, O. F., Jr.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some Effects of Roll Rate on the Longitudinal Stability Characteristics of the Hughes Falcon Missile, ''C'' Configuration, for a Mach Number Range of 1.1 to 1.8 as Determined from Flight Test

Some Effects of Roll Rate on the Longitudinal Stability Characteristics of the Hughes Falcon Missile, ''C'' Configuration, for a Mach Number Range of 1.1 to 1.8 as Determined from Flight Test

Date: December 27, 1955
Creator: Baber, H. T., Jr. & Lundstrom, R. R.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some Research on the Lift and Stability of Wing-Body Combinations

Some Research on the Lift and Stability of Wing-Body Combinations

Date: July 2, 1959
Creator: Purser, Paul E. & Fields, E. M.
Description: The present paper summarizes and correlates broadly some of the research results applicable to fin-stabilized ammunition. The discussion and correlation are intended to be comprehensive, rather than detailed, in order to show general trends over the Mach number range up to 7.0. Some discussion of wings, bodies, and wing-body interference is presented, and a list of 179 papers containing further information is included. The present paper is intended to serve more as a bibliography and source of reference material than as a direct source of design information.
Contributing Partner: UNT Libraries Government Documents Department
Some Experimental Heating Data on Convex and Concave Hemispherical Nose Shapes and Hemispherical Depressions on a 30 Deg Blunted Nose Cone

Some Experimental Heating Data on Convex and Concave Hemispherical Nose Shapes and Hemispherical Depressions on a 30 Deg Blunted Nose Cone

Date: March 10, 1958
Creator: Hopko, R. N. & Strass, H. K.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A Transonic Wind-Tunnel Investigation of the Performance and of the Static Stability and Control Characteristics of a 1/15-Scale Model of the Grumman F9F-9 Airplane, Ted No. NACA DE 390

A Transonic Wind-Tunnel Investigation of the Performance and of the Static Stability and Control Characteristics of a 1/15-Scale Model of the Grumman F9F-9 Airplane, Ted No. NACA DE 390

Date: October 1, 1954
Creator: Bielat, R. P.
Description: None
Contributing Partner: UNT Libraries Government Documents Department