X-15 OPERATIONS FLIGHT REPORT

FLIGHT NO: 1-41-65 DATE OF REPORT: 11/22/63

PILOT: Capt. J. Engle DATE OF FLIGHT: 11/14/63

CARRIER AIRCRAFT: B-52 #008 LAUNCH LAKE: Hidden Hills

PURPOSE OF FLIGHT: 1. Pilot Proficiency 2. Optical Degradation Experiment

Demonstration

I. Discussion of Previous Operations

A. The ART 15A mount remained caged in the pitch axis during the previous flight causing some degradation of experiment results. The pitch axis lock solenoid was inoperative after this flight with indications of overheat. Preflight procedures have been revised to allow operation of the weight shifter to compensate for imbalance of the new recording roll which produced a preload of the pitch axis unlock solenoid. An improperly adjusted solenoid was also noted and induced high actuation friction.

B. The KS-25 experiment was sent to Hycon, Los Angeles, California, to verify focus adjustments.

II. Aircraft Configuration Changes A. The ablation material was completely removed from the aircraft since anticipated flight conditions did not represent an adequate test.

B. Engine S/N 107 was removed because of increasing pump/turbine housing seal leakage and the appearance of two pin-hole leaks in the chamber throat. Engine S/N 104 was installed and does not incorporate the auxiliary helium purge system; this engine will be the last engine which does not contain the second stage igniter chamber purge configuration.

The most successful engine operating experience to date, was obtained with engine S/N 107. This engine operated 15 times for 8 flights, 7 ground runs, and one captive igniter idle sequence. The engine accumulated 15 hours, 59.3 seconds during the installation.

C. Ball nose S/N 006 with a revised T.C. arrangement to evaluate Mach 8 temperature conditions was installed in place of ball nose S/N 003. Ball nose S/N 003 incorporated the 70 degree static orifice.

D. A vacuum gage was installed in the KS-25 experiment system to observe the vacuum cycle through the lower window in the closed-out condition.

III. Instrumentation Changes A. Thermocouples were added to monitor APU LN2 cooling vent exhaust temperatures in place of the APU bulk oil temperatures on the telemetered data display. IV Preflight events A. Leakage from the LOX pump discharge flange occurred during the first ground run attempt with engine S/N 104. Seal replacement was accomplished in a difficult working area without engine removal. An acceptable ground run was accomplished on November 7, 1963.

B. Engine lube oil static leakage was noted from the lube oil pressure switch flameshield drain. Leakage during lube pump operation was negligible, and the condition was accepted for flight.

V. Flight Events A. The operation of all systems was normal during the flight.

Approved by: Prepared by:

Perry V. Row Ronald S. Waite

Senior X-15 Project Engineer X-15 Project Engineer