Atmospheric Case 13.1: F-16, Subsonic Altitude Change

Atmospheric scenario 13.1 started with the same initial conditions as atmospheric case 11 but tests an auto-pilot controlled 100 ft altitude increase at t = 5 sec while initially maintaining a subsonic flight 10,000 ft above First Flight Airport on a 45 deg course.


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 13.1: Subsonic Altitude Change
Vehicle F-16
Geodesy WGS-84 rotating
Atmosphere US 1976 STD; no wind
Gravitation J2 Duration 20 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
10,013
Velocity (NED Frame)
(ft/s)		 X Velocity (North)
Y Velocity (East)
Z Velocity (Down) 		400
400
0
Body Attitude (NED Frame)
(deg)
(3-2-1 Rotation)		 Roll
Pitch
Yaw 		0
0
45
Body Angular Rate (NED Frame) [1]
(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 56, the Rate section should specify body-axis quantities relative to the local frame: Volume II Report ↩︎