Engineering topics

Daforno, G.

Publications and source records attributed to Daforno, G..

5 records

NASA NTRS1983

NTF model concept for the X-29A. Part 1: Requirements, guidelines, and design loads

A few Charpy samples containing a transverse EB weld at the V-notch location were produced. Three tensile specimens containing a transverse weld were also produced. These samples were tested at cryogenic temperatures. The welded Charpy samples resulted in average impact values of 20 ft-lb. This average value is as good as the NASA test samples with the base metal. The tensile specimens broke at slightly higher loads than had been calculated. The Charpy specimens did not come up to the prescribed level of 25 ft-lb. The results of the specimen tests are presented.

Daforno, G.↗

NASA NTRS1982

X-29A for NTF wind-tunnel/flight correlations

Considerations and recommendations for correlation are given. Basic tunnel calibration prior to research and development tests is suggested. Areas of concentration include: wing cruise drag and drag rise, wing separation and stall, afterbody and base drag, propulsion effects, vortex flows, cavity flows, and excrescences.

Daforno, G.↗

NASA NTRS1979

Opportunities for supersonic performance gains through non-linear aerodynamics

This paper contains a number of examples wherein basic aerodynamic shapes are shown to achieve improved performance when non-linear effects are taken into account. Analytical, numerical, and experimental results have all been used to demonstrate this conclusion. Improvements in both zero lift drag and drag due to lift have been identified. The results show that the exploitation of these non-linear aerodynamic effects may be a key ingredient of future supersonic aircraft.

Mason, W. H.↗

NASA NTRS1974

Initial development of an ablative leading edge for the space shuttle orbiter

A state-of-the-art preliminary design for typical wing areas is developed. Seven medium-density ablators (with/without honeycomb, flown on Apollo, Prime, X15A2) are evaluated. The screening tests include: (1) leading-edge models sequentially subjected to ascent heating, cold soak, entry heating, post-entry pressure fluctuations, and touchdown shock, and (2) virgin/charred models subjected to bondline strains. Two honeycomb reinforced 30 pcf elastomeric ablators were selected. Roughness/recession degradation of low speed aerodynamics appears acceptable. The design, including attachments, substructure and joints, is presented.

Daforno, G.↗

NASA NTRS1973

Initial development of an ablative leading edge for the Space Shuttle orbiter.

A state-of-the-art preliminary design for typical wing areas is developed. Seven medium-density ablators (with/without honeycomb, flown on Apollo, Prime, X15A2) are evaluated. The screening tests include (1) leading-edge models sequentially subjected to ascent heating, cold soak, entry heating, post-entry pressure fluctuations, and touchdown shock, and (2) virgin/charred models subjected to bondline strains. Four materials (none molded) are found acceptable. The ESA 3560 HF and MOD 7 Hc (an AVCO 30 pcf elastomer) are selected. Roughness/recession degradation of low speed aerodynamics appears acceptable. The design, including attachments, substructure and joints, is presented.

Daforno, G.↗