X-15 OPERATIONS FLIGHT REPORT

FLIGHT NO: 3-42-65 DATE OF REPORT: 6-10-65

PILOT: Capt. Joe Engle DATE OF FLIGHT: 5-28-65

CARRIER AIRCRAFT: B-52 #008 LAUNCH LAKE: Delamar

ENGINE NO: S/N 107 APU #1 14 APU #2 23

PURPOSE OF FLIGHT: 1. NSL Radiometer

2. Langley Scanner
3. Boundary Layer Noise

I. Discussion of Previous Operations

A. At the request of NAA, the MLG drag-links and snubber were instrumented for this flight. The toe bungees are to be strain gaged in the near future. This data is to aid in the design of improved drag link snubbers and toe bungees. A MLG uplock hook is also being strain gaged for installation. II. Aircraft Configuration Changes A. Engine S/N 111 was removed due to a leak in the chamber tubes at the throat. Engine S/N 107 was installed. A review of engine data taken during the flight showed sticky metering valve operation which would have caused rejection of the engine had not the leak occurred.

B. The fitting of the lightweight tailcone was completed for use when the tailcone box is not required.

C. The RH inner windshield was replaced due to discoloration in the laminations. The windshield was later returned from NAA as serviceable due to there being no mechanical deterioration, only optical.

D. The H2O2 jettison valve was changed for sticking.

E. The Lox safety valve was changed for leakage through the valve. The first valve installed was changed due to a scratch on the flange allowing external leakage.

F. The #l APU metering valve was found to have a short between the heater wiring and the control wiring and was changed. This could have contributed to the prelaunch shutdown on the last flight.

G. The SAS pump shuttle valve was changed to correct a pump overspeed problem.

III. Instrumentation Configuration Changes A. The instrumented drag link snubbers were installed.

B. The instrumentation control lead was moved from the #2 APU switch to a switch added to the canopy panel. This switch was used to control the radiometer.

C. The Nortronics radiometer (experiment #3B) was attached to the back of the tailcone.

D. The Langley Scanner (experiment #4) was installed inside the tailcone box, including a Millikan camera.

E. Base pressure pickups were added to the rear of the rudder. This was accomplished while the rudder was off for other work. Actual recording of the pressures will not start for several flights.

F. A microphone to measure boundary layer noise was added to the rudder using the skin friction gage mount. A total pressure probe was added just aft of the microphone on the removable panel.

G. The Mach probe was removed from the left hand wing tip to be sent to the vendor for repair.

H. The nose gear door bracket strain gages were changed and the brackets recalibrated.

I. The lower bugeye camera was not flown.

IV. Preflight Events A. A satisfactory engine run was accomplished on May 3, 1965.

B. On May 5, the flight schedule was slipped to May 13 due to other X-15 slippages.

C. On May 6, the Langley Scanner alignment to the aircraft was determined.

D. APU and BCS runs were accomplished on May 10, 1965.

E. On May 13, the flight was slipped to May 25 due to B-52 unavailability.

F. The aircraft was again preflighted starting May 14, 1965.

G. The following LN2 lines in the elevator area were checked for corrosion per NAA request, no corrosion was found. 240-53391-161; 240-53390-81, -13, -113; 240-53392 113, -115.

H. APU and BCS runs were repeated on May 24, 1965.

I. Flight was slipped to May 27 due to B-52 unavailability, then to May 28 due to conflict with B-70 schedule.

J. The aircraft was mated for flight on May 27, 1965.

V. Flight Events A. Flight 3-42-65 was accomplished on May 28, 1965, with no problems.
Approved By: Prepared by:

Perry V. Row Vincent N. Capasso

X-15 Senior Project Engineer X-15 Project Engineer