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-37 -34 -29 -3 26 79 30 86 187
-36 -32 -26 -2 28 82 31 88 190
-34 -30 -22 -1 30 86 32 90 194
-33 -28 -18 0 32 90 33 92 198
-32 -26 -15 1 34 93 34 94 201
-31 -24 -11 2 36 97 36 96 205
-30 -22 -8 3 38 100 37 98 208
-29 -20 -4 4 40 104 38 100 212
-28 -18 0 6 42 108 39 102 216
-27 -16 3 7 44 111 40 104 219
-26 -14 7 8 46 115 41 106 223
-24 -12 10 9 48 118 42 108 226
-23 -10 14 10 50 122 43 110 230
-22 -8 18 11 52 126 44 112 234
-21 -6 21 12 54 129 46 114 237
-20 -4 25 13 56 133 47 116 241
-19 -2 28 14 58 136 48 118 244
-18 0 32 16 60 140 49 120 248
Reissue A
P/N 13772-001 5-15
Cirrus Design Section 5
SR22 Performance Data
Outside Air Temperature
for
ISA Condition
Example:
Pressure Altitude...................8000 FT
Outside Air Temp....................... 48° F
ISA Condition .................. ISA + 10° C
Press
Alt
Feet
ISA-40°C ISA-20°C ISA ISA+10°C ISA+20°C
°C °F °C °F °C °F °C °F °C °F
SL -25 -13 -5 23 15 59 25 77 35 95
1000 -27 -18 -7 18 13 54 23 72 33 90
2000 -29 -20 -9 16 11 52 21 70 31 88
3000 -31 -24 -11 12 9 48 19 66 29 84
4000 -33 -27 -13 9 7 45 17 63 27 81
5000 -35 -31 -15 5 5 41 15 59 25 77
6000 -37 -34 -17 2 3 38 13 56 23 74
7000 -39 -38 -19 -2 1 34 11 52 21 70
8000 -41 -42 -21 -6 -1 30 10 48 20 66
9000 -43 -45 -23 -9 -3 27 7 45 17 63
10000 -45 -49 -25 -13 -5 23 5 41 15 59
11000 -47 -52 -27 -16 -7 20 3 38 13 56
12000 -49 -56 -29 -20 -9 16 1 34 11 52
13000 -51 -59 -31 -23 -11 13 -1 31 9 49
14000 -53 -63 -33 -27 -13 9 -3 27 7 45
15000 -55 -67 -35 -31 -15 6 -5 23 5 41
16000 -57 -71 -37 -34 -17 2 -7 20 3 38
17000 -59 -75 -39 -38 -19 -2 -9 16 1 34
17500 -60 -76 -40 -40 -20 -3 -10 14 0 32
Figure 5-6
Reissue A
5-16 P/N 13772-001
Section 5 Cirrus Design
Performance Data SR22
Figure 5-7
Stall Speeds
• Note •
• Altitude loss during wings level stall may be 250 feet or more.
• KIAS values may not be accurate at stall.
Conditions: Example:
• Weight .................................. 3400 LB Flaps .....................................Up (0%)
• C.G. ..........................................Noted Bank Angle....................................15°
• Power............................................Idle C.G........................................ Forward
• Bank Angle ...............................Noted
Stall Speed.......... 71 KIAS | 70 KCAS
Weight
LB
Bank
Angle
Deg
STALL SPEEDS
Flaps 0%Full Up
Flaps 50% Flaps 100%Full
Down
KIAS KCAS KIAS KCAS KIAS KCAS
3400
Most
FWD
C.G.
0 70 69 67 64 59 59
15 71 70 68 65 62 60
30 75 74 72 69 66 64
45 84 82 80 76 73 70
60 99 97 95 90 87 84
3400
Most
AFT
C.G.
0 68 67 66 62 61 59
15 69 68 67 63 62 60
30 73 72 71 67 65 63
45 81 79 78 74 72 70
60 96 94 93 88 86 83
Revision A2
P/N 13772-001 5-17
Cirrus Design Section 5
SR22 Performance Data
Wind Components
• Note •
• The maximum demonstrated crosswind is 20 knots. Value not considered limiting.
Conditions: Example:
• Runway Heading...........................10° Wind/Flight Path Angle ................. 50°
• Wind Direction...............................60° Crosswind Component .........12 Knots
• Wind Velocity........................15 Knots Headwind Component..........10 Knots
10°
Tailwind Headwind
0°
ANGLE BETWEEN WIND DIRECTION AND FLIGHT PATH
20°
30°
40°
50°
60°
70°
80°
90°
100°
110°
140° 130° 120°
150°
160°
170°
180°
VELOCITY ~ KNOTS WIND
40
10 20 30 40
WIND COMPONENTS ~ KNOTS
CROSSWIND COMPONENT ~ KNOTS
-20
-10
0
10
20
40
30
SR22_FM05_1014
10
20
30
50
Figure 5-8
Reissue A
5-18 P/N 13772-001
Section 5 Cirrus Design
Performance Data SR22
Takeoff Distance
Factors:
The following factors are to be applied to the computed takeoff
distance for the noted condition:
• Headwind - Subtract 10% from computed distance for each 12
knots headwind.
• Tailwind - Add 10% for each 2 knots tailwind up to 10 knots.
• Grass Runway, Dry - Add 20% to ground roll distance.
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