Paul Croce

The goal of this work was to analyze and observe, in a realistic home setting, fire development from ignition through full room involvement, and the subsequent extinguishment of the fire. A full-scale bedroom facility, similar to that used in the first Home Fire Project bedroom test, was selected and furnished in typical fashion with a resulting fuel load of 4.0 lb/sq ft of floor area. A simulated match ignition of the mattress was used to start the fire; ventilation was provided through a single open doorway. Measurements made during the burn (173 in total) included gas and surface temperatures, heat fluxes, gas velocities, gas species concentrations, optical densities, weight loss, differential pressure, and relative humidity. Following ignition, the fire was observed at first to grow slowly, but steadily, as the mattress became more involved, then more rapidly with full room involvement occurring at approximately 7 min after ignition. This test did not exhibit the change from a growing to a diminishing fire that occurred in the first test when the room became fully involved at approximately 171/2 min after ignition.

Richard Hill

Tests were run to determine the effect of the angle and radius of curvature of a firewall, with respect to a burn-through flame, on burn-through time. No difference was noted in burn-through time for angles of zero-, 10-, or 20 degrees. A slight increase was noted at 30 degrees, and at 40 degrees in burn-through occurred. No great difference in burn-through time was noted with a change in the curvature of the firewall. Centerline flat plate impingement pressures and temperature were measured and graphed for burn-through having pressure ratios of 11:1, 9:1, 6:1, and 4:1, and holes sizes of 1, 1.5, and 2 inches. The exit velocity, density and miss-flow rate were also calculated for those flames. The radial flat plate impingement profile was mapped for an 11:1 pressure ration flame from 1.5-inch hole. Flame characteristics of 16:1, 20:1, and 25:1 pressure ratio burn-through were estimated. Three appendixes are included in this report: (1) The Design of a Standard Burn-Through Simulator; (2) Determination of a Standard Burn-Through Hole Size; and (3) A summary of Burn-Through Work at NAFEC from January 1, 1972, to December 31, 1973, including Results and Conclusions.

Jack J. Shrager

A review of all literature published since 1967 relating to aircraft flight controls and displays was made. Special emphasis was placed on the contents of those documents as they related to the all-weather landing and takeoff operational envelope. The results of this review are evaulated, summarized, and conclusions drawn. This is suppllemented by an annotated bibliography and author's index.

Robert N. Stuckey, Daniel E. Supkis, James Price

Full-scale aircraft cabin flammability tests to evaluate the effectiveness of new fire-resistant materials by comparing their burning characteristics with those of older aircraft materials are described. Three tests were conducted and are detailed. Test 1, using pre-1968 materials, was run to correlate the procedures and to compare the results with previous tests by other organizations. Test 2 included newer, improved fire-resistant materials. Test 3 was essentially a duplicate of test 2, but a smokeless fuel was used. Test objectives, methods, materials, and results are presented and discussed. Results indicate that the pre -1968 materials ignited easily, allowed the fire to spread, produced large amounts of smoke and toxic combustion products, and resulted in a flash fire and major fire damage. The newer fire-resistant materials did not allow the fire to spread. Furthermore, they produced less smoke, lower concentrations of toxic combustion products, and lower temperatures. The newer materials did not produce a flash fire. _

Leo J. Garodz, David Lawrence, Nelson J. Miller

The characteristics of the trailing vortex system of the Boeing 747 airplane have been investigated by the National Aviation Facilities 'Experimental Center (NAFEC) Atlantic City N. J.t during a series of flight tests conducted in September and October 1972. This investigation is part of a long-term programt started in February 1970 with flight tests conducted by NAFEC at the Atomic Energy Commission site at Idaho Fallst Idahot devoted to the study of the overall wake turbulence problem. The present tests were conducted using improved flow measurement and meteorological instrumentationt permitting greater resolution than had been possible in earlier testing. Principal findings were that the peak tangential velocity decays as the reciprocal of the square root of the time elapsed since vortex generation; that the peak velocity is unaffected by the throttling back of the adjacent outboard engine; and that the lateral transport velocities correlate quite well with theory. Vortex descent'rates did not correlate with theorYt being up to three times greater than theoretical values. It was further determined that the velocity distribution in the Bo_ing 747 trailing vortices is strongly affected by the wing flap setting. At small settingst the vortex core diameter is small and peak tangential velocities are hight and as the flap deflection is increasedt the core diameters increase and peak velocities diminish.