Report presenting an exploration of fuel temperatures, which includes variables such as the aircraft speed, flight time, flight altitude, materials of construction, location of fuel tanks relative to aircraft skin and hot engine parts, and other factors. The results illustrate that it is impossible to predict quantitatively the fuel temperatures that will be attained in aircraft without detailed design information on each machine.

Report presenting an experimental airplane crash in order to study the performance of a prototype crash-fire inerting system for reciprocating-engine-powered airplanes. A fire did not occur during this crash, indicating that the crash-fire inerting system functioned satisfactorily as a complete unit. Further improvements in the crash-fire system are also provided.

From Introduction: "This report makes further comparisons of the theoretical computing method with available experimental results, showing effects of wing plan-form changes, and the effect of an airfoil-section change on a wing of given plan form."

"A wind-tunnel investigation was made to determine the effects of ejecting high-velocity air near the leading edge of plain trailing-edge flaps on a 35 degree sweptback wing. The tests were made with flap deflections from 45 degrees to 85 degrees and with pressure ratios across the flap nozzles from sub-critical up to 2.9. A limited study of the effects of nozzle location and configuration on the efficiency of the flap was made. Measurements of the lift, drag, and pitching moment were made for Reynolds numbers from 5.8 to 10.1x10(6)" (p. 1).

"Aerodynamic forces and moments have been obtained in the Langley 9- by 12-inch blowdown tunnel on an external store and on a 45 degree swept-back wing-body combination measured separately at Mach numbers from 0.70 to 1.96. The wing was cantilevered and had an aspect ratio of 4.0; the store was independently sting-mounted and had a Douglas Aircraft Co. (DAC) store shape. The angle of attack range was from -3 degrees to 12 degrees and the Reynolds number (based on wing mean aerodynamic chord) varied from 1.2 x10(6) to 1.7 x 10(6)" (p. 1).

"Low-lift drag data are presented herein for one 1/7.5-scale rocket-boosted model and three 1/45.85-scale equivalent-body models of the Grumman F9F-9 airplane, The data were obtained over a Reynolds number range of about 5 x 10(exp 6) to 10 x 10(exp 6) based on wing mean aerodynamic chord for the rocket model and total body length for the equivalent-body models. The rocket-boosted model showed a drag rise of about 0,037 (based on included wing area) between the subsonic level and the peak supersonic drag coefficient at the maximum Mach number of this test" (p. 1).

Report presenting a linear stability analysis and flight-test investigation on a rolleron-roll-rate stabilization system for a canard missile. This type of damper provides roll damping by the action of gyro-actuated uncoupled wing-tip ailerons. A dynamic roll instability predicted by the analysis was confirmed by flight testing and was subsequently eliminated by introducing control-surface damping about the rolleron hinge line.