Atmospheric Case 12: F-16, Supersonic Trim Flyout

Atmospheric scenario 12 tests a straight and level supersonic flight at an altitude 30,000 ft above First Flight airport on a 45 deg course at 2000 ft/s (approximately Mach 2) [1] through still air.

The vehicle was trimmed for level, un-accelerated flight by varying pitch attitude, elevator position, and throttle setting before allowing the open-loop vehicle to fly for 180 sec.


Constants and Models

This scenario uses a F-16 vehicle model, specified here. The 1976 STD atmosphere model defines atmospheric properties at various altitudes, specified here. The F-16's source of gravity is the J2 gravity model, specified here. The geodesy model used for this scenario is the WGS-84 rotating model, specified here.


Initial Conditions

Scenario Atmospheric Case 12: Supersonic Winged Flight
Vehicle F-16
Geodesy WGS-84 rotating
Atmosphere US 1976 STD; no wind
Gravitation J2 Duration 180 s
Initial states
Aerodynamic Characteristics
 S (ft2)
b (ft)
c (ft)
Additional Aerodynamic Characterstics Specified Here 		300.0
30.0
11.32
Geodetic Position
(deg, deg, ft MSL)		 Latitude
Longitude
Altitude, Mean Sea Level 		36.01916667
-75.67444444
30,013
Velocity (NED Frame)
(ft/s)		 X Velocity (North)
Y Velocity (East)
Z Velocity (Down) 		1414.213562
1414.213562
0
Body Attitude (NED Frame)
(deg)
(3-2-1 Rotation)		 Roll
Pitch
Yaw 		0
0
45
Body Angular Rate (NED Frame) [2]
(deg/s)		 Roll Rate
Pitch Rate
Yaw Rate 		0
0
0

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Errata

Below is the list of erratum that are relevant to changes made on this page that no longer match the report. The full list can be found on the Home Page.

[1] Page 63, Section C.1.12, Paragraph 1, change from "Mach 20" to "approximately Mach 2": Volume II Report ↩︎

[2] Page 56, the Rate section should specify body-axis quantities relative to the local frame: Volume II Report ↩︎