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Aerodynamic Demonstration Tests |
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| MIL-D-23222A(AS)
AERODYNAMIC DEMONSTRATION TESTS
3.8
GENERAL
3.8.1
GROSS WEIGHT AND CENTER-OF-GRAVITY POSITIONS. - The
3.8.1.1
maximum aft and maximum forward center-of-gravity
positions shall be the maximum positions that can be obtained with any
service loading combination attainable as defined in Spec MIL-W-25140.
The gross weight for a specified center-of-gravity position shall be
approximately that corresponding to a service loading which would
occur with the specified center-of-gravity position. Where neither
the weight nor the center-of-gravity position is specified, a combina-
tion representative of planned service use of the helicopter shall be
used.
FLYING QUALITIES
3.8.2
OPERATING FLIGHT ENVELOPE - Flying qualities tests
3.8.2.1
shall consist of quantitative flight-test measure-
ments demnonstrating compliance with selected requirements of Spec MIL-
H-8501A which are outlined in Table 3. The terminology used in the
Demonstration will
table is that employed in Spec MIL-H-8501.
ordinarily be required at two altitudes selected as the highest and
the lowest altitude at which demonstration of each required maneuver
is significant and practical.
CONFIGURATION. - Except where indicated, all demon-
3.8.2.2
stration tests shall be performed in the normal
helicopter configuration, i.e., with stability augmentation, and powered
or boosted control system operating.
MAXIMUM PERMISSIBLE SPEED ENVELOPE. - The flight
3.8.2.3
characteristics shall be such as to permit the
limits required for structural demonstration to be accomplished to the
extent that those limits are included in contract structural design
requirements.
PERFORMANCE - Demonstration of performance shall
3.8.3
include those tests necessary to determine that the
helicopter can meet the contract performance guaranteed items specified
in the Detail Specification. The following items shall be included in
the performance demonstration:
(1) At normal take-off weight, power required in level
flight throughout the speed range shall be deter-
mined at sea level at three different rpm's closen
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