National Advisory Committee for Aeronautics (NACA) - 13,786 Matching Results

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Primary view of Aerodynamic Characteristics of Two Rectangular-plan-form, Allmovable Controls in Combination With a Slender Body of Revolution at Mach Numbers From 3.00 to 6.25
Wong, Thomas J. & Gloria, Hermilo R.
December 28, 1955
Primary view of An Analysis of a Nuclear Powered Supercritical-Water Cycle for Aircraft Propulsion
Karp, Irving M.
January 19, 1953
Primary view of Nonuniform Burnup and Poisoning Effects in a Reactor and Validity of Uniform Approximation
Spooner, Robert B.
March 9, 1953
Primary view of The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselagestore Configurations 1. - Swept-Wing Heavy-Bomber Configuration With Large Store (Nacelle). Lift and Drag; Mach Number, 1.61
Smith, Norman F. & Carlson, Harry W.
March 11, 1955
Primary view of Performance at Mach Numbers 3.07, 1.89, and 0 of Inlets Designed for Inlet-Engine Matching Up to Mach 3
Gertsma, L. W. & Beheim, M. A.
May 20, 1958
Primary view of Summary of Subsonic-Diffuser Data
Henry, John R.; Wood, Charles C. & Wilbur, Stafford W.
October 12, 1956
Primary view of Combustion Performance of Two Experimental Turbojet Annular Combustors at Conditions Simulating High-Altitude Supersonic Flight
Zettle, Eugene V.; Norgren, Carl T. & Mark, Herman
March 26, 1954
Primary view of Wind-Tunnel Investigation at Subsonic and Supersonic Speeds of a Model of a Tailless Fighter Airplane Employing a Low-Aspect-Ratio Swept-Back Wing-Stability and Control
Smith, Willard G.
January 12, 1953
Primary view of Performance of Isentropic Nose Inlets at Mach Number of 5.6
Bernstein, Harry & Haefeli, Rudolph C.
May 6, 1954
Primary view of Rocket-Model Investigation of the Rolling Effectiveness of a Fighter-Type Wing-Control Configuration at Mach Numbers From
Strass, H. Kurt & Marley, Edward T.
February 25, 1952
Primary view of Free-flight Tests of 45 Deg Swept Wings of Aspect Ratio 3.15 and Taper Ratio 0.54 to Measure Wing Damping of the First Bending Mode and to Investigate the Possibility of Flutter at Transonic Speeds
O'Kelly, Burke R.; Lundstrom, Reginald R. & Lauten, William T., Jr.
October 12, 1954
Primary view of The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselage-store Configurations 2 - Swept-wing Heavy-bomber Configuration With Large Store Nacelle. Lateral Forces and Pitching Moments, Mach Number, 1.61
Smith, Norman F. & Carlson, Harry W.
July 6, 1955
Primary view of The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselagestore Configurations 6. - Swept-Wing Heavy-Bomber Configuration With Stores of Different Sizes and Shapes
Smith, Norman F.
March 8, 1956
Primary view of Additional Experiments With Flat-Top Wing- Body Combinations at High Supersonic Speeds
Syvertson, Clarence A.; Wong, Thomas J. & Gloria, Hermilo R.
February 19, 1957
Primary view of Dynamic Stability Investigation of Two Right Circular Cylinders in Axial Free Flight at Mach Numbers From 0.4 to 1.7 Fineness-Ratio- 2.56 Cylinder and Fineness-Ratio-4.0 Cylinder With Flared Afterbody
McFall, John C., Jr.
February 28, 1957
Primary view of Effects of Wing-Fuselage Flow Fields on Missile Loads at Subsonic Speeds
Alford, William J., Jr.
June 27, 1955
Primary view of Investigation of Aerodynamic Characteristics of an Airplane Configuration Having Tail Surfaces Outboard of the Wing Tips at Mach Numbers of 2.30, 2.97, and 3.51
Church, James D.; Hayes, William C., Jr. & Sleeman, William C., Jr.
June 23, 1958
Primary view of Investigation of Lithium Hydride and Magnesium as High-Temperature Internal Coolants With Several Skin Materials
Modisette, Jerry L.
May 28, 1958
Primary view of Investigation of High-Angle-of-Attack Performance of a 14 Deg Ramp-Type Inlet in Various Circumferential Body Locations: Mach Number Range 1.5 to 2.0
Mitchell, Glenn A. & Chiccine, Bruce G.
June 26, 1957
Primary view of Effects of Modifications to a Control Surface on a 6-Percent-Thick Unswept Wing on the Transonic Control-Surface Flutter Derivatives
Wyss, John A.; Sorenson, Robert M. & Gambucci, Bruno J.
May 2, 1958
Primary view of Force and Pressure-Distribution Investigation to High Angles of Attack on All-Movable Triangular and Rectangular Wings in Combination With a Body at Supersonic Speeds
Hill, William A., Jr. & Kaattari, George E.
July 10, 1956
Primary view of A Note on the Ability to Predict Transonic Drag-Rise Changes Due to Model Modifications
Pierpont, P. Kenneth
October 3, 1957
Primary view of Some Considerations Regarding the Application of the Supersonic Area Rule to the Design of Airplane Fuselages
Whitcomb, Richard T.
July 3, 1956
Primary view of A Summary of Results Obtained During Flight Simulation of Several Aircraft Prototypes With Variable-Stability Airplanes
McNeill, Walter E. & Creer, Brent Y.
May 25, 1956
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