Technical Report Archive and Image Library (TRAIL) - 22,044 Matching Results

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Effects of Inlet Modification and Rocket-Rack Extension on the Longitudinal Trim and Low-Lift Drag of the Douglas F5D-1 Airplane as Obtained with a 0.125-Scale Rocket-Boosted Model Between Mach Numbers of 0.81 and 1.64: TED No. NACA AD 399

Description: A flight investigation was conducted to determine the effects of inlet modification and rocket-rack extension on the longitudinal trim and low-lift drag of the Douglas F5D-1 airplane. The investigation was conducted with a 0.125-scale rocket-boosted model between Mach Numbers of 0.81 and 1.64. This paper presents the changes in trim angle of attack, trim lift coefficient, and low-lift drag caused by the modified inlets alone over a small part of the test Mach number range and by a combination of the modified inlets and extended rocket racks throughout the remainder of the test.
Date: June 5, 1957
Creator: Hastings, Earl C., Jr. & Dickens, Waldo L.
Partner: UNT Libraries Government Documents Department

Static Longitudinal and Lateral Stability Characteristics of an 0.065-Scale Model of the Chance Vought XRSSM-N-9a (REGULUS II) Missile at Mach Numbers from 1.6 to 2.0 (TED No. NACA AD 3122)

Description: The static longitudinal and lateral stability charaetefistics of an 0.065-scale model of the XRSSM-N-9a (REGULUS II) Missile at Mach number range of 1.6 to 2.0 at a Reynolds number per foot of 2.0(exp 8).
Date: June 6, 1957
Creator: Hofstetter, William R.
Partner: UNT Libraries Government Documents Department

Recent data on tire friction during landing

Description: From Summary: "An investigation was made at the Langley landing-loads track to obtain data on the coefficient of friction during wheel spin-up. A landing gear was tested at horizontal velocities ranging from 0 to 180 feet per second together with vertical velocities of 7.0 and 9.3 feet per second. The results indicate the effect of forward speed and tire inflation pressure on the coefficient of friction."
Date: June 7, 1957
Creator: Batterson, Sidney A.
Partner: UNT Libraries Government Documents Department

The use of wind tunnels to predict flight buffet loads

Description: From Summary: "Methods and techniques developed for the study of buffeting by use of wind-tunnel models are described. Requirements on model damping and frequency characteristics, the model support system, and the effects of wind-tunnel turbulence on buffet tests are outlined. The results are shown of a recent comparison of buffet loads measured on a research airplane with thin unswept wings and on two different models of the airplane in two different wind tunnels."
Date: June 10, 1957
Creator: Davis, Don D., Jr. & Huston, Wilber B.
Partner: UNT Libraries Government Documents Department

Analytical study of the comparative pitch-up behavior of several airplanes and correlation with pilot opinion

Description: From Introduction: "An extension of the work presented in reference 2, the method was applied to six swept-wing airplanes for which the pilot opinion was well documented. The analytical results obtained are used herein to illustrate how wind-tunnel data may be used to predict the pitching motions and the comparative pitch-up behavior of new airplane designs or to assess the effects of modifications on existing airplanes."
Date: June 12, 1957
Creator: Sadoff, Melvin; Stewart, John D & Cooper, George E
Partner: UNT Libraries Government Documents Department

Aerodynamic Heating and Boundary-layer Transition on a 1/10-power nose shape in free flight at Mach numbers up to 6.7 and Free-stream Reynolds numbers up tp 16 x 10(exp 6)

Description: Report presenting testing of a modified 1/10-power nose shape in free flight at Mach numbers up to 6.7. Measured heating rates were presented and compared with calculated values. Results regarding transition and comparison with previous investigations are provided.
Date: June 17, 1957
Creator: Garland, Benjamine J.; Swanson, Andrew G. & Speegle, Katherine C.
Partner: UNT Libraries Government Documents Department

Heat transfer measured on a flat-face cylinder in free flight at Mach numbers up to 13.9

Description: Report presenting an investigation of a five-stage rocket model at mach number 13.9 and an altitude of 81,500 feet. Temperatures were measured at 12 stations on the flat-face copper nose. Heating rates calculated from temperature time histories are compared to theoretical predictions of the rates.
Date: June 17, 1957
Creator: Stoney, William E., Jr. & Swanson, Andrew G.
Partner: UNT Libraries Government Documents Department