In Cruise segment:
Treq
9226 lb
Tavail
11845 lb
CL RCr ,V CTS
0.37 deg. 0.4979 567.8 nm
Range at constant Altitude:
For aircraft equipped with jet engines: 1.677 1 CL AR Rh CTS WCr WCr WFCr cJ S w CD
Eqn.(1)
The airplane drag coefficient is calculated from: C D C D 0,Clean BDPclean C L2AR
Eqn.(2)
The optimum lift coefficient during the cruise for aircraft equipped with jet engine is defined as: CLopt
max R
CD 0,Clean 3BDPClean
Eqn.(3)
The constant flight speed during cruise is calculated from:
U1
2WCr WFCr
C L S w
Eqn.(4)
AR
C LAR
0.4150
Treq
9226 lb
Tavail
11845 lb
U1 C Lopt , MaxR
0.37 deg 475.00 kts. 0.4157
RCr ,h CTS Altitude
2849.7 nm 37800 ft.
10