曝光臺 注意防騙 網(wǎng)曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

ETAS = Effective True Airspeed AD = Air Distance
T = Time between DRs ZN = Crosswind Displacement
D2 = Second "D" reading D1 = First "D" reading
BD = Bellamy Drift GD = Ground Distance
or K = 21.49 / sin (Latitude)
or Equivalent True Air Speed = Air Distance / Elapsed Time
392 AFPAM11-216 1 MARCH 2001
or ZN = K * (D2 – D1) / Equivalent True Air Speed
or Bellamy Drift = ZN * 57.3 / Ground Distance
A2.5. TAS/Mach:
Variables:
CAS = Calibrated Airspeed M = Mach
IT = Indicated Air Temperature CT = Temperature Rise (+1 for most aircraft)
TAT = True Air Temperature (°Celsius) DA = Density Altitude
PA = Pressure Altitude TAS = True Airspeed
or MACH = sq rt (5 * ((( 1 / ( ( (518.67 – (0.003566 * Pressure Altitude) ) / 518.67 ) ^5.2563 )) *
((1 + 0.2 * (Calibrated Air Speed /661.5)^2 ) ^ 3.5 – 1 ) + 1) ^ .286) – 1)
or MACH = True Air Speed / ( 39 * sq rt (Temperature Celsius + 273) )
or Calibrated Air Speed = 661.5 * sq rt ((((((( 1 + (MACH^2) / 5 ) ^ (1/0.286) ) – 1 ) *
(((518.67 – (0.003566 * Pressure Altitude)) / 518.67 ) ^ 5.2563 )
+ 1 ) ^ (1/3.5)) – 1 ) / 0.2)
Indicated Air Speed = Calibrated Air Speed * F_Factor
or True Air Speed = 39 * MACH * sq rt ( (Indicated Air Temperature + 273) *
((Temperature Rise * ((1 / (1 + 2. * MACH^2)) – 1)) + 1))
NOTE: Temperature Rise is generally +1 degree for most aircraft
or True Air Speed = 39 * MACH * sq rt (True Air Temperature)
NOTE: True Air Temperature is in degrees Kelvin (Celsius + 273.15)
A2.6. Turn Performance:
Variables:
BANK = Bank Angle
DIAM = Turn Diameter in NM
T = Time to Complete 360° turn
AFPAM11-216 1 MARCH 2001 393
or Turn Diameter = True Air Speed^2 / (34208 * tan (Bank Angle) )
or Minutes for Complete 360 = .0055 * True Air Speed / tan (Bank Angle)
GForce = 1 / cos (Bank Angle)
Turn Stall Speed = Normal Stall Speed * GForce
A2.7. Celestial Precomputations:
Variables:
LAT = Latitude of Assumed Position or DR LONG = Longitude of Assumed Position or DR
Zn = True Azimuth Z = Azimuth Angle
Hc = Height Computed DEC = Declination of the Body from Air Almanac
SHA = Sidereal Hour Angle
LHA = Local Hour Angle = GHA –W (+E) Long + SHA + corrections
NOTE: Hc and Z will be displayed in degrees and decimal degrees. You must convert the decimal
degrees to minutes. Once the azimuth angle (Z) has been determined by computation, the ambiguity
caused by LAT and LHA can be resolved by the following:
Zn = Z sin (LHA)<0
Zn = 360 – Z sin (LHA)>0
or Height Computed (Hc) = asin ( sin (DR Latitude) * sin (Body_Declination) + cos(LHA) *
cos(Body_Declination) * cos(DR Latitude) )
or Azimuth Angle = acos (( sin (Body_Declination) – sin (DRL altitude) * sin (Height Computed ))/
( cos (Height Computed ) * cos (DRL altitude)))
Zn = Z N LAT and LHA > 180°
Zn = 360 – Z N LAT and LHA < 180°
Zn = 180 – Z S LAT and LHA > 180°
Zn = 180 + Z S LAT and LHA < 180°
394 AFPAM11-216 1 MARCH 2001
MOTIONS:
The formula for combined 1–minute motion can be separated as follows:
or Motion of Body = 15 (cos (LAT)(sin Zn)
or Motion of the Body (for 1 minute) = 15 * cos (Latitude) * sin (Azimuth)
or Motion of the observer (for 1 minute) = (Ground Speed / 60) * cos (True Course – Azimuth)
These quantities, whether combined or used separately, must be added algebraically to the Ho and
subtracted from the Hc. To apply Coriolis/rhumb line correction to Ho, multiply Coriolis/rhumb line by
sin (ZN–TC). Note that P and N adjustments are not necessary with these computer applications since
Hc is correct for fix time, not Pub. No. 249 EPOCH year time.
or Motion of the Body (for 1 minute) = 15 * cos (Latitude) * sin (Azimuth) –
(cos (True Course – Azimuth) * Ground Speed / 60)
or Motion of the Body (for 1 minute) = 15 * cos (Latitude) * cos (270–Azimuth) –
(cos (True Course – Azimuth) * Ground Speed / 60)
or Rhumb Line = 0.146 * (Ground Speed /100)^2 * sin (True Course) * tan (Latitude)
or Coriolis = 0.02625 * Ground Speed * sin (Latitude)
or Coriolis = cos (90 – True Course – Azimuth) * 0.02625 * Ground Speed * sin (Latitude)
For combined Coriolis/rhumb line adjustment to assumed position, use:
or Coriolis = 0.02625 * Ground Speed * sin (Latitude) +
[0.146 * (Ground Speed /100)^2 * sin (True Course) * tan(Latitude)]
AFPAM11-216 1 MARCH 2001 395
A2.8. Great Circle Planning:
Variables:
L1 = Departure Latitude (N and W = +) L2 = Destination Latitude (S and E = –)
l1 = Departure Longitude l  2 = Destination Longitude
　
中國航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：F16 Flying Operations AIR NAVIGATION(161)