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open access

Wind-Tunnel Investigation at Low Speed of Sideslipping, Rolling, Yawing, and Pitching Characteristics for a Model of a 45 Degree Swept-Wing Fighter-Type Airplane

Description: Report presenting an investigation in the stability tunnel at low speed to determine the rolling characteristics at combined angles of attack and sideslip for a model of a fighter-type airplane with a 45 degree sweptback wing. Testing was performed with the original vertical tail and a vertical tail with a 27 percent larger exposed area. Results regarding the static longitudinal stability, directional stability, and effect of the different tails are presented.
Date: September 1, 1955
Creator: Jaquet, Byron M. & Fletcher, H. S.
open access

Investigation of a high-pressure-ratio eight-stage axial-flow research compressor with two transonic inlet stages 6: over-all performance, rotating stall, and blade vibration at low and intermediate compressor speeds

Description: Report presenting an investigation to determine the overall performance of the modified eight-stage axial-flow compressor with new fourth-stage stator blades as part of a study of the problems encountered in a high-pressure-ratio axial-flow compressor with transonic inlet stages. The performance of the compressor was determined over a range of weight flows at equivalent speeds from 30 to 100 percent of design speed.
Date: November 1, 1955
Creator: Standahar, Raymond M.; Hanson, Morgan P. & Geye, Richard P.
open access

Longitudinal Aerodynamic Characteristics at Transonic Speeds of a Complete Model With an Unswept Wing and a Sweptback Horizontal Tail at Two Vertical Locations

Description: Memorandum presenting an investigation to determine the static longitudinal stability contribution of a horizontal tail at two vertical locations behind a 4-percent-thick unswept-wing-fuselage combination at transonic speeds. The model used in tests is comprised of an unswept wing located in the midwing position on a body of revolution and a sweptback horizontal tail mounted on a vertical tail.
Date: September 1, 1955
Creator: Hieser, Gerald & Kudlacik, Louis
open access

Spark ignition of flowing gases 5: application of fuel-air-ratio and initial-temperature data to ignition theory

Description: Report presenting a study to show the effect of fuel-air ratio and initial temperature on spark-ignition energy and to apply the results to a previously developed theory of ignition. Results regarding initial-temperature effect and fuel-air-ratio effect are provided.
Date: November 1, 1955
Creator: Swett, Clyde C., Jr.
open access

Hydrodynamic Pressure Distribution Obtained With a Streamline Body Equipped With Chine Strips

Description: Memorandum presenting an investigation to determine the nature of the pressure distribution and the order of magnitude of the pressures on a streamline body moving on a water surface. The body of revolution was equipped with chine strips and had a fineness ratio of 9. The results from the investigation indicate that there is a characteristic pattern of hydrodynamic pressure distribution for streamline bodies equipped with chine strips and moving on a water surface.
Date: September 1, 1955
Creator: Weinflash, Bernard
open access

Comparative Dispersion Data From Ground-Launched 2.25-Inch Rockets Equipped With Cruciform and Monoplane Fins

Description: Report presenting testing of about 150 rounds of 2.25-inch subcaliber aircraft rockets equipped with standard cruiform fins and twisted monoplane fins. No significant difference in dispersion was observed for the different configurations of fins on the rockets. Results regarding the stability of the different types of rockets, and general characteristics of the flight paths are provided.
Date: November 1, 1955
Creator: Purser, Paul E.
open access

Low-Speed Wind-Tunnel Tests of a 1/8-Scale Model of the Bell D-188A VTOL Airplane

Description: Report discussing the results of an investigation to determine the low-speed power-off stability and control characteristics of a model of the Bell D-188A VTOL airplane. The static stability and control characteristics were generally satisfactory except above certain angles of attack and aileron effectiveness dropped off as the angle of attack was increased. Modifications for increasing the directional stability by altering the vertical tails are also described.
Date: August 1, 1958
Creator: McKinney, Marion O. & Smith, Charles C., Jr.
open access

Effect of Reduced Stator-Blade Trailing-Edge Thickness on Over-All Performance of a Transonic Turbine

Description: "A transonic turbine with a stator trailing-edge thickness reduced from 0.030 to 0.010 inch has been investigated experimentally. The performance results indicated an increase in efficiency of 0.6 of a point at design operation, and as much as 2.4 points at off-design conditions, as a result of reducing the trailing-edge thickness. This improvement could only be partially accounted for by the theoretical change in mixing loss for the two stator-blade rows, and it was felt that the improvement w… more
Date: November 1, 1955
Creator: Whitney, Warren J.; Stewart, Warner L. & Wong, Robert Y.
open access

Investigation of Power Requirements for Ice Prevention and Cyclical De-Icing of Inlet Guide Vanes with Internal Electric Heaters

Description: "An investigation was conducted to determine the electric power requirements necessary for ice protection of inlet guide vanes by continuous heating and by cyclical de-icing. Data are presented to show the effect of ambient-air temperature, liquid-water content, air velocity, heat-on period, and cycle times on the power requirements for these two methods of ice protection. The results showed that for a hypothetical engine using 28 inlet guide vanes under similar icing conditions, cyclical de-ic… more
Date: December 1, 1950
Creator: von Glahn, Uwe & Blatz, Robert E.
open access

An Investigation of the Afterbody Pressure Distribution and Fin Loading Characteristics of a Specialized Store Configuration at Transonic Speeds

Description: Report presenting an investigation in the transonic pressure tunnel to determine the afterbody pressure distribution and fin loading characteristics of two configurations of the TX-21 special weapon. The only different in the two configurations was the nose contour, with one having a hemispherical-flat shape and one with a double-radius ogive-flat shape. Results regarding the pressure port, fin loads, and force measurements are provided.
Date: August 1, 1956
Creator: Henry, Beverly Z., Jr. & Braden, John A.
open access

Performance of Several Half-Conical Side Inlets at Supersonic and Subsonic Speeds

Description: Report discussing an evaluation of a series of half-conical side inlets mounted on the fuselage of a supersonic aircraft at various Mach numbers. Information about the maximum total-pressure recovery, asymmetrical operation of the twin-duct system, potential reduction in stable mass-flow range, boundary-layer diverter height, and engine mass flow is described.
Date: February 1, 1956
Creator: Stitt, Leonard E.; Cubbison, Robert W. & Flaherty, Richard J.
open access

Afterburner Performance With Combustion-Chamber Lengths From 10 to 62 Inches at Several Afterburner-Inlet Temperatures

Description: Effect of variation of combustion chamber length and inlet temperature on low pressure-loss sea level afterburner. A 70-percentage-point reduction in combustion efficiency resulted when the combustion-chamber length was reduced from 62 to 10 inches.
Date: February 1, 1956
Creator: Ciepluch, Carl C.; Velie, Wallace W. & Burley, Richard R.
open access

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

Description: Report presenting an investigation of the aerodynamic characteristics of a model of the Grumman F9F-9 airplane in the transonic tunnel. Results regarding the transonic drag-rise increment, drag analysis, and effective downwash angle are provided.
Date: October 1, 1954
Creator: Bielat, Ralph P.
open access

Wind-Tunnel Measurement of Static Forces on Internally Carried Bombs of Two Different Bluff Shapes in the Flow Field of a Swept-Wing Fighter-Bomber Configuration at a Mach Number of 1.6

Description: Report discussing the influence of forces and moments on a fighter-bomber airplane with an open bomb bay and on two bluff bomb shapes in various positions below the fuselage and plane of symmetry. The wing was found to have a noticeable effect on bomb forces and that bluff bombs affect the longitudinal characteristics of the wing-fuselage combination.
Date: April 1, 1957
Creator: Geier, Douglas J. & Robins, A. Warner
open access

First Landing of Bell X-2 Research Airplane

Description: Report presenting testing regarding the Bell X-2 supersonic research airplane, which is equipped with a skid main landing gear and nose wheel, to determine the low-speed handling qualities and landing characteristics. Results regarding the landing approach pattern, time histories, and final resting position of the airplane at landing are provided.
Date: October 1, 1952
Creator: Day, Richard E. & Stillwell, Wendell H.
open access

An Investigation of the Longitudinal Characteristics of the X-3 Configuration Using Rocket-Propelled Models: Preliminary Results at Mach Numbers From 0.65 to 1.25

Description: Report presenting a rocket-powered model of the X-3 configuration flown through a range of Mach numbers to determine the response of the model to rapid deflections of the horizontal tail and its effects on lift, drag, longitudinal stability and control, and longitudinal-trim change. The model was found to remain statically and dynamically stable through the lift-coefficient and Mach number range of the test.
Date: December 1, 1950
Creator: Mitchell, Jesse L. & Peck, Robert F.
open access

Performance of J35-A-23 Compressor 1: Over-All Performance Characteristics at Equivalent Speeds From 20 to 100 Percent of Design

Description: Report presenting an investigation of the overall performance of the J35-A-23 compressor, which is a 16-stage compressor designed to produce a total-pressure ratio of 8.75 at an equivalent flow of 155 pounds per second and an equivalent speed of 6100 rpm. Tests were run at a range of flows and speeds. Notes on installation and characteristics of the compressor are also provided.
Date: October 1, 1951
Creator: Medeiros, Arthur A.; Guentert, Donald C. & Hatch, James E.
open access

Analysis of V-g records from the Grumman F8F-2 airplane

Description: From Introduction: "In the present paper, which supplements reference 1, V-g records obtained from F8F-2 airplanes in 1949 are analyzed statistically to determine the frequency of experiencing large values of normal load factor and airspeed. These results are compared with the results from the F8F-1 airplane."
Date: July 1, 1952
Creator: Thornton, James O.
open access

An Investigation at Transonic Speeds of the Aerodynamic Characteristics of an Air Inlet Installed in the Root of a 45 Degree Sweptback Wing

Description: Report presenting an investigation in the transonic blowdown tunnel from Mach numbers 0.80 to 1.41 to determine the increments in lift and drag due to installation of a triangular-shaped air inlet in the root of a 45 degree sweptback wing and to determine the internal flow characteristics of the inlet. Results regarding pressure measurements of the inlet model, force measurements of basic and inlet models, and effect of boundary-layer bypass scoop and fuselage nose configuration on characterist… more
Date: October 1, 1952
Creator: Howell, Robert R. & Keith, Arvid L., Jr.
open access

Stability and Control Flight Tests of a 0.13-Scale Model of the Consolidated-Vultee XFY-1 Airplane in Take-Offs, Landings, and Hovering Flight: TED No. NACA DE 368

Description: Report presenting an investigation to determine the dynamic stability and control characteristics of a scale flying model of the Consolidated-Vultee XFY-1 vertically rising airplane. It includes the results of flight tests to determine the stability and control characteristics of the model in hovering, take-offs, and landings.
Date: October 1, 1952
Creator: Lovell, Powell M., Jr.; Smith, Charles C., Jr. & Kirby, Robert H.
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