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The Subsonic Lateral and Longitudinal Static Stability Characteristics Up to Large Angles of Sideslip for a Triangular-Wing Airplane Model Having a Ventral Fin

Description: "Wind-tunnel tests were conducted to determine the effects of a ventral fin on the static characteristics of a triangular-wing airplane model. Data were obtained for angles of sideslip up to 18 degrees at angles of attack of 0, 6, 12, and 18 degrees at Mach numbers from 0.25 to 0.94. The results of the tests indicated that the ventral fin did not produce as much yawing moment per unit of exposed area at any angle of sideslp as the vertical tail" (p. 1).
Date: October 25, 1956
Creator: Buell, Donald A. & Tinling, Bruce E.
Partner: UNT Libraries Government Documents Department

The Results of Wind-Tunnel Tests at Low Speeds of a Four-Engine Propeller-Driven Airplane Configuration Having a Wing With 40 Degrees of Sweepback and an Aspect Ratio of 10

Description: Report presenting a wind-tunnel investigation to study the effects of operating propellers on the low-speed longitudinal characteristics of a four-engine tractor airplane configuration. The coefficients of lift, longitudinal force, pitching moment, propeller thrust, and propeller power are provided. Tests were conducted at a range of Mach and Reynolds numbers.
Date: December 21, 1953
Creator: Edwards, George G.; Buell, Donald A. & Dickson, Jerald K.
Partner: UNT Libraries Government Documents Department

The Subsonic Lateral and Longitudinal Static Stability Characteristics Up to Large Angles of Sideslip for a Triangular-Wing Airplane Model Having a Ventral Fin

Description: "Wind-tunnel tests were conducted to determine the effects of a ventral fin on the static characteristics of a triangular-wing airplane model. Data were obtained for angles of sideslip up to 18 degrees at angles of attack 0, 6, 12, and 18 degrees at Mach numbers from 0.25 to 0.94. The results of the tests indicated that the ventral fin did not produce as much yawing moment per unit of exposed area at any angle of sideslip as the vertical tail" (p. 1).
Date: October 25, 1956
Creator: Buell, Donald A. & Tinling, Bruce E.
Partner: UNT Libraries Government Documents Department

The Static and Dynamic-Rotary Stability Derivatives at Subsonic Speeds of an Airplane Model With an Unswept Wing and a High Horizontal Tail

Description: Report presenting measurements in a wind tunnel of the static and dynamic-rotary stability derivatives of a model with an unswept wing of low aspect ratio and a high horizontal tail. Tests were conducted at a range of Mach numbers and angles of attack. Results regarding a variety of aerodynamic characteristics are provided.
Date: December 5, 1956
Creator: Buell, Donald A.; Reed, Verlin D. & Lopez, Armando E.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of the Effects of a Jet Engine Nacelle on the Aerodynamic Characteristics of a 37.25 Degree Swept Back Wing at High Subsonic Speeds

Description: Report presenting a wind-tunnel investigation to determine the aerodynamic characteristics of a wing-nacelle combination at high subsonic speeds. Lift, drag, pitching-moment, and ram-recovery data re presented for a range of Mach and Reynolds numbers.
Date: October 24, 1950
Creator: Boltz, Frederick W. & Buell, Donald A.
Partner: UNT Libraries Government Documents Department

The Effects at Subsonic Speeds of Wing Fences and a Tail on the Longitudinal Characteristics of a 63 Degree Swept-Wing Fuselage Combination

Description: Report presenting wind-tunnel testing to evaluate the effects of wing fences and a tail on the longitudinal characteristics of a highly swept wing in combination with a fuselage. The model, which had a cambered and twisted wing with a leading-edge sweepback of 63 degrees and an aspect ratio of 3.5, was tested with fences of various shapes and swept and unswept horizontal tails. Results regarding exploratory tests, final-configuration tests, static longitudinal stability factors, and maximum lift-drag ratios are provided.
Date: July 2, 1957
Creator: Buell, Donald A. & Kolbe, Carl D.
Partner: UNT Libraries Government Documents Department

The Effect of an Operating Propeller on the Aerodynamic Characteristics of a 1/10-Scale Model of the Lockheed XFV-1 Airplane at High Subsonic Speeds (TED No. NACA DE-377)

Description: "An investigation was conducted in the Ames 12-foot pressure wind tunnel to determine the effect of an operating propeller on the aerodynamic characteristics of a 1/19-scale model of the Lockheed XFV-1 airplane. Several full-scale power conditions were simulated at Mach numbers from 0.50 to 0.92; the.Reynolds number was constant at 1.7 million. Lift, longitudinal force, pitch, roll, and yaw characteristics, determined with and without power, are presented for the complete model and for various combinations of model components" (p. 1).
Date: May 6, 1952
Creator: Sutton, Fred B. & Buell, Donald A.
Partner: UNT Libraries Government Documents Department

The Effect of an Operating Propeller on the Aerodynamic Characteristics at High Subsonic Speeds of a Model of a Vertical-Rising Airplane Having an Unswept Wing of Aspect Ratio 3

Description: Report presenting an investigation in the pressure wind tunnel to determine the effect of an operating propeller on the aerodynamic characteristics of a model of a vertical-rising airplane with an unswept wing with an aspect ratio of 3. Lift, longitudinal force, pitch, and roll characteristics, with and without power, are presented for the complete model and various combinations of model components.
Date: November 15, 1954
Creator: Sutton, Fred B. & Buell, Donald A.
Partner: UNT Libraries Government Documents Department

Analysis of Wind-Tunnel Tests at Low Speeds of a Four-Engine Propeller-Driven Airplane Configuration Having a Wing With 40 Degrees of Sweepback

Description: Report presenting an investigation to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane with a 40 degree swept wing with an aspect ratio of 10. Results regarding components of the lift changes due to operating propellers, components of the pitching-moment changes due to operating propellers, effect of configuration changes on the pitching-moment characteristics of the model, stick-fixed longitudinal stability of the model, reduction of adverse effects of propellers on longitudinal stability, and propulsive characteristics are provided.
Date: October 8, 1954
Creator: Edwards, George G. & Buell, Donald A.
Partner: UNT Libraries Government Documents Department

Investigation of an NACA 4-(5)(05)-041 Four-Blade Propeller With Several Spinners at Mach Numbers Up to 0.90

Description: Report presenting an investigation to determine the aerodynamic characteristics of an NACA 4-(5)(05)-041 four-blade propeller in combination with NACA 1-series and extended cylindrical spinners for a range of blade angles. Results regarding variation of propeller thrust coefficient, power coefficient, efficiency, tip Mach number, characteristics of the propeller in combination with different spinners, and maximum efficiency are provided.
Date: December 24, 1952
Creator: Reynolds, Robert M.; Buell, Donald A. & Walker, John H.
Partner: UNT Libraries Government Documents Department

Ground Effects on the Longitudinal Characteristics of Two Models With Wings Having Low Aspect Ratio and Pointed Tips

Description: Wind-tunnel tests were conducted to determine the ground effects on a tailless model with a wing of aspect ratio 2 and infinite taper, and on a tailed model with a triangular wing of aspect ratio 3, with flaps. Control-surface hinge moments were measured on the tailless model. The results are compared with the predictions of the theory of Tani, et al.
Date: July 1957
Creator: Buell, Donald A. & Tinling, Bruce E.
Partner: UNT Libraries Government Documents Department

Analysis of Wind-Tunnel Tests to a Mach Number of 0.90 of a Four-Engine Propeller-Driven Airplane Configuration Having a Wing With 40 Degrees of Sweepback and an Aspect Ratio of 10

Description: Report presenting an investigation at speeds of up to Mach number 0.90 to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane configuration with a 40 degree swept wing with an aspect ratio of 10. Results regarding low-speed conditions, high-speed conditions, components of lift, effect of configuration changes, longitudinal stability, and the reduction of adverse effects of propellers on stability are provided.
Date: September 1956
Creator: Edwards, George G.; Buell, Donald A.; Demele, Fred A. & Sutton, Fred B.
Partner: UNT Libraries Government Documents Department