National Advisory Committee for Aeronautics (NACA) - Browse

ABOUT BROWSE FEED

Drag measurements at low lift of a four- nacelle airplane configuration having a longitudinal distribution of cross-sectional area conductive to low transonic drag rise

Description: Drag measurements at low lift of four-nacelle aircraft configuration with longitudinal distribution of cross-sectional area conducive to low transonic drag rise.
Date: November 18, 1953
Creator: Hall, J. R.; Hopko, R. N. & Piland, R. O.
Partner: UNT Libraries Government Documents Department

A Feasibility Study of the Flare-Cylinder Configuration as a Reentry Body Shape for an Intermediate Range Ballistic Missile

Description: A study has been made of a flare-cylinder configuration to investigate its feasibility as a reentry body of an intermediate range ballistic missile. Factors considered were heating, weight, stability, and impact velocity. A series of trajectories covering the possible range of weight-drag ratios were computed for simple truncated nose shapes of varying pointedness, and hence varying weight-drag ratios. Four trajectories were chosen for detailed temperature computation from among those trajectories estimated to be possible. Temperature calculations were made for both "conventional" (for example, copper, Inconel, and stainless steel) and "unconventional" (for example, beryllium and graphite) materials. Results of the computations showed that an impact Mach number of 0.5 was readily obtainable for a body constructed from conventional materials. A substantial increase in subsonic impact velocity above a Mach number of 0.5 was possible without exceeding material temperature limits. A weight saving of up to 134 pounds out of 822 was possible with unconventional materials. This saving represents 78 percent of the structural weight. Supersonic impact would require construction of the body from unconventional materials but appeared to be well within the range of attainability.
Date: May 28, 1958
Creator: Garland, B. J. & Hall, J. R.
Partner: UNT Libraries Government Documents Department

Experimental and Theoretical Determination of Forces and Moments on a Store and on a Store- Pylon Combination Mounted on a 45 Deg Swept- Wing-Fuselage Configuration at a Mach Number of 1.61

Description: Forces and moments of store-pylon combination mounting on swept wing-fuselage configuration in supersonic pressure tunnel.
Date: January 30, 1958
Creator: Carlson, H. W.; Geier, D. J. & Morris, O. A.
Partner: UNT Libraries Government Documents Department

Boundary-Layer-Transition and Heat-Transfer Measurements from Flight Tests of Blunt and Sharp 50 Degree Cones at Mach Numbers from 1.7 to 4.7

Description: Boundary-layer-transition and heat-transfer measurements were obtained from flight tests of blunt and sharp cones having apex angles of 50 deg. The test Mach number range was from 1.7 to 4.7, corresponding to free-stream Reynolds numbers, based on cone base diameter, of 18. 3 x 10(exp 6) and 32.1 x 10(exp 6), respectively. Transition on both models occurred at a local Reynolds number of 1 x 10(exp 6) to 2 X 10(exp 6) based on distance from the stagnation point. Transition Reynolds numbers based on momentum thickness were between 320 and 380 for the blunt cone. The model surface roughness was 25 rms microinches or greater. Turbulent heat transfer to the conical surface of the blunt cone at a Mach number of 4 was 30 percent less than that to the surface of the sharp cone. Available theories predicted heat-transfer coefficients reasonably well for the fully laminar or turbulent flow conditions.
Date: April 18, 1957
Creator: Chauvin, Leo T. & Speegle, Katherine C.
Partner: UNT Libraries Government Documents Department