getting to grips with aircraft performance 如何掌握飞机性能 2(16)

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62  85.5 .780 1357 302 170.1 462  85.6 .780 1279 289 178.8 458  85.9 .780 1214 277 186.8 454  86.3 .780 1158 264 194.1 450  87.6 .780 1135 252 197.1 447  90.1 .780 1153 241 194.0 447 
64  85.7 .780 1373 302 168.2 462  85.9 .780 1297 289 176.4 458  86.2 .780 1234 277 183.8 454  86.7 .780 1182 264 190.2 450  88.2 .780 1170 252 191.2 447 
66  86.0 .780 1389 302 166.2 462  86.2 .780 1316 289 173.9 458  86.6 .780 1254 277 180.9 454  87.2 .780 1209 264 186.0 450  89.0 .780 1209 252 185.0 447 
68  86.2 .780 1406 302 164.2 462  86.5 .780 1335 289 171.4 458  86.9 .780 1275 277 177.9 454  87.8 .780 1242 264 181.0 450  89.8 .780 1252 252 178.7 447 
70  86.5 .780 1424 302 162.1 462  86.8 .780 1355 289 168.9 458  87.3 .780 1299 277 174.6 454  88.4 .780 1277 264 176.1 450  90.8 .780 1298 252 172.3 447 
72  86.8 .780 1442 302 160.0 462  87.1 .780 1375 289 166.4 458  87.7 .780 1325 277 171.2 454  89.0 .780 1314 264 171.1 450 
74  87.1 .780 1462 302 157.9 462  87.5 .780 1397 289 163.9 458  88.2 .780 1357 277 167.1 454  89.8 .780 1356 264 165.7 450 
76  87.4 .780 1482 302 155.8 462  87.8 .780 1419 289 161.3 458  88.8 .780 1392 277 162.9 454  90.5 .780 1400 264 160.5 450 
LOW AIR CONDITIONING wFUEL = . 0.5 %  ENGINE ANTI ICE ON wFUEL=+2%  TOTAL ANTI ICE ON wFUEL=+5% 
Figure F27: Cruise table example

 

G. CLIMB
1. FLIGHT MECHANICS
1.1. Definitions
The following Figure (G1) shows the different forces applied on an aircraft in
climb.

. The angle of attack (α
) represents the angle between the aircraft axis and the aerodynamic axis (speed vector axis tangent to the flight path).

. The climb gradient (γ
) represents the angle between the horizontal axis and the aerodynamic axis.

. The aircraft attitude (θ
) represents the angle between the aircraft axis and the horizontal axis (in a ground reference system).

. 
The rate of climb (RC) represents the vertical component of the aircraft’s speed. It is positive and expressed in feet per minute.

1.2. Climb Equations
During climb at constant speed, the balance of forces is reached. Along the aerodynamic axis, this balance can be expressed as :
(1) Thrust cosα= Drag + Weight sinγ
1 In order to simplify, the thrust vector is represented parallel to the aircraft longitudinal axis.

The balance along the vertical axis, becomes :
(2) Lift = Weight cosγ
1.2.1. Climb Gradient (γ
)
The climb gradient (γ) and the angle of attack (α) are usually small enough so that :
sinγ≈ tanγ≈γ (in radian) cosγ≈ 1 and cosα≈ 1
　
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