MEMORANDUM for Chief, Research Projects Office
After launch, the heading hold mode of the adaptive flight control system was engaged on a heading of approximately 223.5 degrees instead of the planned 215 degrees. This heading deviation placed the X-15 to the right of the planned flight track. Maximum altitude attained was approximately 237,000 ft. A pushover maneuver prior to shutdown resulted in the peak altitude below the planned 260,000 feet.
The Langley Scanner experiment requires that pitch attitude be maintained at zero degrees or slightly negative above 212,000 ft. Pitch attitude during the scanner data acquisition period was decreasing from approximately 10 to 2.6 degrees. During this interval, 14 scans were made. These data appear usable although the requested flight conditions were not attained.
Boundary layer noise data were requested for a constant dynamic pressure at approximately 650 psf, however, this pressure was not maintained. Some boundary layer noise data may have been obtained during dynamic pressure of 400 to 500 psf.
Although listed on the flight request, no attempt was made to obtain horizontal tail loads on this flight. The aircraft is instrumented and a checkout of equipment operation is scheduled for flight 3-52.
The following discrepancies were noted for this flight:
b. The TDM and FM power was below normal during the flight. This problem is under investigation.
c. Oscillograph 0-21-36C ran out of film shortly after touchdown. This oscillograph was turned on early in flight to include the airborne analyzer check of the adaptive flight control system.
d. Hydrogen peroxide
leakage from the roll rockets was noted during the prelaunch ballistic
control system check. Following the flight, these valves were removed from
the aircraft. Analysis failed to indicate the source of the malfunction.
The valves were assembled and checked during the BCS checks for preflight.
These valves appear to be functioning normally.
Elmor J. Adkins, Head
X-15 Research Project Office