MIL-M-8555C
3.9.3.3 Aerodynamics. The following characteristics of the airframe
aerodynamics shall be specified and all sources of performance data shall be
identified (ie, wind tunnel data, analytical data, etc).
Lift forces
a.
(1)
Lift
coefficient versus angle of attack.
(2)
Lift
slope variation with math.
(3)
Wing
and body lift distribution.
(4)
Wing
and control surface loadings from trimmed lift.
b.
Drag forces
(1) Profile drag versus math number.
(2) Induced drag versus lift coefficient.
(3) Drag versus altitude and Mach number throughout the flight
envelope.
(4) Interference drag and boat tail drag effects.
Control moments
c.
(1) Pitch (yaw) moment clue to angle of attack.
(2) Pitch (yaw) moment due to control surface motion.
(4) Control surface hinge moments.
Stability
d.
(1) Static stability margin, loaded and empty condition.
(2) Dynamic stability margin, in flight conditions.
3.9.4 Propulsion subsystem. The following performance and physical
characteristics of the propulsion subsystem shall be specified:
Physical characteristics
a.
(1) Type (rocket, ramjet, or combination of rocket and ramjet).
(2) Dimensions.
(3) Weight and center of gravity before and after burn.
Performance
b.
(1)
Specific impulse (motor-fuel).
(2)
Total thrust.
Time-thrust and time-impulse profiles.
(3)
(4)
Burn rate versus soak temperatures.
(5)
Mass fraction and density.
(5)
Thermal stability.
(7)
Altitude and speed effects on performance.
(8)
Angle of attack restrictions (due to flameout).
(9)
Maneuverability restrictions (due to flameout).
(10)
Special environmental conditions (including storage).
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