29 research outputs found
Effect of Conical and Flat Sting-mounted Windshields on the Zero-lift Drag of a Flare-stabilized Bluff Body at Mach Numbers from 0.6 to 1.15
Free-flight Investigation of Jet Effect on the Low-lift Drag and Longitudinal Trim of a Supersonic Interceptor-type Airplane Configuration with an Overhanging Tail Boom at Mach Numbers from 1.09 to 1.34
A Flight Investigation to Determine the Effectiveness of Mach Number 1.0, 1.2, and 1.41 Fuselage Indentations for Reducing the Pressure Drag of a 45 Degree Sweptback Wing Configuration at Transonic and Low Supersonic Speeds
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NACA Research Memorandums
Report presenting drag data obtained from flight tests of two scale rocket-powered models of the Chance Vought XF8U-1 airplane. Results regarding the minimum drag coefficient and effect of nose modifications are provided
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NACA Research Memorandums
Memorandum presenting low-lift drag and longitudinal trim data for two versions of an interceptor-type airplane, the second of which had a slimmer nose and a thinner tail than the first. Data are presented for three models (complete, wingless, and horizontal tailless) of the first version, and from one model (complete configuration) of the second version. Results regarding longitudinal trim, drag, longitudinal stability, and flutter and buffet are provided
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NACA Research Memorandums
Report presenting drag and longitudinal trim characteristics at low lift of a low-tail version of the North American YF-100A airplane as obtained from the flight test of a 0.11-scale rocket model at a range of Mach numbers. Longitudinal stability data and some qualitative damping-in-pitch data are also provided
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NACA Research Memorandums
Report presenting longitudinal trim and drag at low lift of the North American YF-100A airplane at a range of Mach numbers as obtained with rocket-propelled models for an airplane, with the horizontal tail removed, and with wing removed conditions. Results regarding drag, longitudinal trim, longitudinal stability, and flutter and buffet are provided
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NACA Research Memorandums
Drag and longitudinal trim at low lift of the North American YF-100A airplane at Mach numbers from 0.76 to 1.77 as determined from the flight test of a 0.11-scale rocket model are presented herein. Also included are some longitudinal stability and some qualitative pitch-damping data
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NACA Research Memorandums
Report presenting zero-lift drag data for a flare-stabilized bluff body of fineness ratio 4.4 alone and with conical and flat windshields at a range of Mach and Reynolds numbers. The model with the flat windshield was found to have the lowest drag at Mach numbers up to 1.05, but there was little difference in drag among the models above 1.05
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NACA Research Memorandums
Report presenting a rocket-powered free-flight model of an interceptor-type airplane with an overhanging tail boom with the jet on and off at a range of Mach numbers. Results regarding longitudinal trim, drag, and lift are provided