FLIGHT NO: 3-39-62 DATE OF REPORT: 2-10-65
PILOT: Milt Thompson DATE OF FLIGHT: 1-13-65
CARRIER AIRCRAFT: B-52 #003 LAUNCH LAKE: Hidden Hills
ENGINE NO: S/N 103 APU #1 16 APU #2 20
PURPOSE OF FLIGHT: 1. Non-uniform, 3 Dimension Flow Field
Measurements
2. Surface Discontinuity Heat Transfer Test3. Skin Friction
4. Boundary Layer Noise
5. Landing Gear Door Modification Checkout
I. Discussion of Previous Operations
B. The second stage pressure sensing system for the cockpit indicator was revised. The transducer and amplifier were eliminated and a pressure transmitter used similar to main chamber pressure. The H2O2 tank pressure sensing system was deleted and the amplifier removed (has been inoperative for several months).
C. The mixing chamber temperature indicator was replaced with a single needle standard AF unit utilizing resistance bulb probes. Switching between #l and #2 mixing chamber indication is accomplished by a switch mounted in the straddle panel.
D. The pin which held the skid banjo fitting to the bottom of the struts was changed from a 240 to a 2581 pin (stronger pin).
E. The engine transducer mounting bracket was installed in the top of the engine bay while the engine was removed for item IV A.
F. Standard F-3 and F-4 panels were installed, the test panels F-31 (reference panel) and F-32 (240-931525-11, small waves) were not changed.
B. The nose gear strut was disassembled due to oil seepage past the seals. Bits of bronze from the upper bearing were found imbedded in the "0" rings, new "0" rings were installed. The wear on the upper bearing is due to score marks in the upper cylinder reported as item IV D of flight report 3-31-52. There has been no spare strut available since the strut was replaced after flight 3-29-48 (see flight report 3-30-50).
C. An APU run was accomplished on January 8, 1965. The RH APU, S/N 23, had a gear case oil leak and was replaced by APU S/N 20. A satisfactory APU run was accomplished on January 9, 1965.
D. The aircraft was weighed on January 11, 1965 just prior to mating. Aircraft weight empty (or basic weight) was determined to be 13,940 pounds.
E. Mating for flight was accomplished on January 11, 1965.
F. Flight was not attempted on January 12, 1965 due to Air Force support aircraft problems.
Perry V. Row Vincent N. Capasso
X-15 Senior Project Engineer X-15 Project Engineer