Performance Data for Cirrus SR22 G6

Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile. Cruise climbs or short duration climbs are permissible at best power as long as altitudes and temperatures remain within those specified in the table. For operation in air colder than this table provides, use coldest data shown. For operation in air warmer than this table provides, use caution. CLIMB GRADIENT - Feet per Nautical Mile Temperature ~ °C Weight Press Climb Alt Speed FT KIAS -20 0 20 40 50 ISA SL 97 646 583 526 473 448 540 2000 96 547 488 435 385 362 458 4000 95 453 398 348 302 281 380 6000 94 363 312 266 223 203 306 3150 8000 94 278 231 188 148 129 233 10000 93 198 154 114 77 59 164 12000 92 122 81 43 9 98 14000 91 49 11 #24 56 71 35 SL 93 857 780 710 645 615 727 2000 92 737 666 600 540 512 629 4000 92 623 557 496 440 414 535 6000 91 516 454 397 345 321 445 2600 8000 90 414 356 304 255 233 359 10000 89 317 264 215 170 149 276 12000 88 226 176 131 89 70 198 14000 88 140 93 51 12 6 123 P/N 11934-005 Original Issue 5-19 Section 5 Performance Data Enroute Rate of Climb Conditions: ⚫ Power .. • Mixture....... " Flaps....... • Airspeed Cirrus Design SR20 Full Throttle Per Placard .0% (UP) Best Rate of Climb • Note ⚫ Rate-of-Climb values shown are change in altitude in feet per unit time expressed in Feet per Minute. For operation in air colder than this table provides, use coldest data shown. For operation in air warmer than this table provides, use caution. Cruise climbs or short duration climbs are permissible at best power as long as altitudes and temperatures remain within those specified in the table. Aircraft with optional Air Conditioning System: Maximum rate of climb performance is reduced by approximately 75 feet per minute if system is ON. For maximum climb performance the air conditioner should be off. Weight RATE OF CLIMB Feet per Minute Temperature ~ °C Press Alt Climb Speed LB FT KIAS 20 20 40 50 ISA SL 97 968 908 849 789 760 864 2000 96 843 783 723 663 633 750 4000 95 719 657 596 535 505 636 6000 94 594 532 469 407 376 522 3150 8000 94 469 405 341 278 247 408 10000 93 344 278 212 148 116 294 12000 92 218 150 83 17 15 180 14000 91 91 21 -48 -115 148 66 SL 97 1279 1211 1143 1075 1041 1160 2000 96 1133 1065 995 927 893 1026 4000 95 988 918 848 778 744 893 6000 94 842 771 699 629 594 760 2600 8000 94 697 624 551 479 444 627 10000 93 551 476 402 329 293 494 12000 92 405 328 252 177 141 362 14000 91 258 179 101 26 12 230 5-20 P/N 11934-005 Original Issue Cirrus Design SR20 Section 5 Performance Data Enroute Rate of Climb Vs Density Altitude • Conditions: • • Power.. ⚫ Mixture Flaps Airspeed. .Full Throttle Per Placard 0% (UP) Best Rate of Climb 15,000 3150 LB 14,000 13,000 12,000 11,000 10,000 9000 8000 7000 6000 5000 4000 3000 2000 1000 Density Altitude - Feet 0 2600 LB P/N 11934-005 Original Issue 100 200 300 400 500 600 700 800 002. Rate of Climb ~ Feet Per Minute `900 1000 1200 1100 SR20 FM05_5418 5-21 Section 5 Performance Data Time, Fuel and Distance to Climb Conditions: • Power ⚫ Mixture. ⚫ Fuel Density........... Cirrus Design SR20 Full Throttle Per Placard ..6.0 LB/GAL ° Weight ..... ⚫ Winds..... ° Climb Airspeed ⚫ Note • 3150 LB ......Zero .. Noted Taxi Fuel - Add 1.5 gallon for start, taxi, and takeoff. Temperature - Add 10% to computed values for each 10° C above standard. Fuel flow must be set to the placarded limit for all takeoffs and climbs. Cruise climbs or short duration climbs are permissible at best power as long as altitudes and temperatures remain within those specified in the table. Rate Of TIME, FUEL, DISTANCE – From Sea Level Press OAT Climb Alt (ISA) Speed Climb Time Fuel Distance Minutes U.S. Gal NM FT C KIAS FPM SL 15 97 864 0.0 0.0 0 1000 13 96 807 1.2 0.4 2 2000 11 96 750 2.6 0.8 4 3000 9 95 693 4.0 1.3 7 4000 7 95 636 5.6 1.7 9 5000 LO 5 95 579 7.3 2.3 12 6000 3 94 522 9.2 2.8 15 7000 1 94 465 11.4 3.4 19 8000 -1 94 408 13.8 4.1 23 9000 -3 93 351 16.7 4.8 28 10000 -5 93 294 20.1 5.7 35 11000 -7 92 237 24.3 6.8 42 12000 -9 92 180 29.9 8.2 52 13000 -11 92 123 38.0 10.1 67 14000 -13 91 66 53.2 13.6 96 5-22 P/N 11934-005 Original Issue Cirrus Design SR20 Cruise Performance Conditions: Mixture. ° Weight. ⚫ Winds... Section 5 Performance Data .Target Fuel Flow* 2600 LB Zero Shaded Cells: Cruise Pwr above 85% not recommended. *For power settings greater than 75% power, Best Power. • Note • Subtract 10 KTAS if nose wheel pant and fairing removed. Lower KTAS by 10% if nose and main wheel pants and fairings are removed. Aircraft with optional Air Conditioning System: Cruise performance is reduced by 2 knots. For maximum performance, turn air conditioner off. Aircraft with optional Enhanced Vision System: Cruise performance is reduced by up to 1 knot. Press ISA -30°C ISA® Alt RPM MAP PWR 2000 2700 271 94% 151 2500 27 1 86% 148 14.9 82% 151 ISA +30°C KTAS GPH PWR KTAS GPH PWR |KTAS GPH 16.5 90% 156 158 85% 158 15.2 13.7 14.2 78% 153 2500 26.0 81% 145 14.2 77% 148 13.6 73% 150 11.5 2500 24.9 77% 142 13.5 73% 144 12.3 69% 146 10.9 2500 23.8 72% 139 13.3 68% 140 11.6 65% 142 10.3 2500 22.7 67% 2500 21.6 62% 2500 20.5 58% 2500 19.4 53% 4000 2700| 25.2 | 88% 2500 25.2 80% 135 12.5 64% 130 11.7 59% 126 11.0 55% 121 10.2 50% 152 15.6 84% 147 14.1 76% 136 10.9 61% 138 9.7 132 10.3 56% 127 9.6 52% 132 9.1 127 8.5 2500 24.1 76% 144 13.4 72% 121 9.0 48% 155 14.9 80% 150 146 12.0 68% 121 8.0 157 14.4 13.4 73% 152 11.2 148 10.6 2500 23.0 71% 2500 21.9 66% 136 140 13.0 67% 142 11.3 64% 144 10.0 12.2 | 63% 138 10.6 60% 139 9.4 2500 19.7 57% 2500 20.8 61% 132 127 11.4 58% 133 9.9 55% 134 10.6 | 54% 8.8 128 9.3 51% 128 8.2 2500 18.6 52% 121 9.9 49% 2500 17.5 47% 115 9.1 45% 122 115 8.6 47% 122 7.7 8.0 42% 115 7.1 P/N 11934-005 Original Issue 5-23 Section 5 Performance Data Press ISA -30°C ISA Cirrus Design SR20 ISA + 30°C Alt RPM MAP PWR |KTAS GPH | PWR KTAS GPH PWR |KTAS GPH 6000 2700 23.4 82% 151 14.7 78% 154 14.1 74% 156 11.4 2500 23.4 75% 146 13.5 71% 148 11.7 68% 150 10.4 2500 22.3 70% 142 12.7 66% 144 11.0 63% 145 9.7 2500 21.2 65% 138 11.9 62% 140 10.3 59% 141 9.1 2500 20.1 60% 133 11.1 57% 135 9.7 55% 136 8.6 2500 19.0 56% 128 10.3 53% 129 9.0 50% 129 8.0 2500 17.9 51% 2500 16.8 46% 8000 2700 21.6 76% 2500 21.6 70% 2500 20.5 65% 2500 19.4 60% 2500 18.3 55% 123 9.6 48% 123 8.4 46% 123 7.4 116 8.8 44% 116 7.7 42% 115 6.9 150 13.9 72% 152 11.9 69% 154 10.5 144 12.5 66% 140 11.6 61% 146 10.8 63% 148 | 9.5 142 10.1 58% 143 8.9 135 10.9 57% 137 9.4 54% 137 8.4 130 10.1 52% 131 8.8 50% 131 7.8 2500 17.2 50% 124 9.3 48% 124 8.1 45% 124 7.2 10000 2700 | 20.0 2500 16.1 45% 71% 117 8.6 43% 117 7.5 41% 116 | 6.7 148 12.7 67% 150 11.0 64% 151 9.7 2500 20.0 65% 142 11.5 61% 144 10.0 58% 145 8.8 2500 18.9 60% 138 10.7 56% 139 9.3 54% 139 8.2 2500 17.8 55% 132 9.9 52% 133 8.6 49% 133 7.6 14000 2700 | 17.1 61% 12000 2700 18.5 2500 18.5 60% % 140 10.6 57% 2500 17.4 55% 135 9.8 52% 2500 16.3 50% 128 9.0 47% 2500 15.2 45% 121 8.3 43% 143 10.8 57% 2500 16.7 50% 126 2500 15.6 45% 119 8.4 66% 6 9.1 47% 126 8.0 45% 126 7.1 43% 118 7.3 41% 117 6.5 146 11.7 62% 147 10.1 59% 148 8.9 141 9.2 54% 142 8.1 135 8.5 49% 135 7.5 128 7.9 45% 128 6.9 120 7.2 40% 119 6.4 144 9.3 54% 145 8.2 2500 17.1 55% 137 9.8 52% 138 8.5 50% 138 7.5 2500 16.0 50% 131 9.0 48% 131 7.8 45% 130 6.9 2500 14.9 45% 123 8.2 43% 123 7.1 41% 121 6.3 5-24 P/N 11934-005 Original Issue Cirrus Design SR20 Range / Endurance Profile Conditions: • • Weight...... Temperature. Winds. ⚫ Mixture • Total Fuel…... Section 5 Performance Data 3000 LB . Standard Day Zero See Tables ....56 Gallons Note " Fuel Remaining For Cruise accounts for 10.1 gallons for 45 minutes IFR reserve fuel at 75% power and fuel burn for descent. Range and endurance shown includes descent to final destination at 160 KIAS and 500 fpm. Range is decreased by 5% if nose wheel pant and fairings removed. For aircraft with optional Air Conditioning System: range is decreased by 1% if system in operation. Range is decreased by 15% if nose and main wheel pants and fairings removed. 75% POWER Mixture = Target Fuel Flow Press Climb | Alt Fuel Fuel Remaining For Cruise Airspeed Fuel Endurance Range Specific Flow Range FT Gal Gal KTAS GPH Hours NM Nm/Gal 0 0.0 47.9 144 12.3 3.9 558 11.6 2000 0.8 47.2 146 12.1 3.9 574 12.1 4000 1.7 46.4 149 12.0 3.9 588 12.5 6000 2.8 45.5 8000 4.1 44.3 10000 5.7 42.7 12000 8.2 40.4 14000 13.6 35.0 P/N 11934-005 Original Issue 5-25 Section 5 Performance Data Range / Endurance Profile (Continued) Cirrus Design SR20 | 65% POWER Mixture = Target Fuel Flow Press Climb Alt Fuel Fuel Remaining Airspeed Fuel Endurance Range Specific Flow Range For Cruise Gal Gal KTAS GPH Hours NM Nm/Gal 0.0 47.9 135 10.9 4.4 596 12.4 2000 0.8 47.2 138 10.7 4.4 613 12.9 4000 1.7 46.4 140 10.5 4.4 629 13.4 6000 2.8 45.5 143 10.3 4.4 643 13.8 8000 4.1 44.3 145 10.2 4.3 655 14.4 10000 5.7 42.7 12000 8.2 40.4 14000 13.6 35.0 55% POWER Mixture = Target Fuel Flow Press Climb Fuel Airspeed Fuel Endurance Range Specific Alt Fuel Remaining Flow Range For Cruise Gal Gal KTAS GPH Hours NM Nm/Gal 0 0.0 47.9 125 9.5 5.1 630 13.2 2000 0.8 47.2 127 9.3 5.1 651 13.7 4000 1.7 46.4 130 9.1 5.1 670 14.2 6000 2.8 45.5 132 9.0 5.1 687 14.8 8000 4.1 44.3 135 8.8 5.0 700 15.3 10000 5.7 42.7 137 8.7 4.9 709 15.8 12000 8.2 40.4 139 8.6 4.7 709 16.3 14000 13.6 35.0 5-26 P/N 11934-005 Original Issue 1 Cirrus Design SR20 Balked Landing Climb Gradient Conditions: ⚫ Power..... * Mixture 5 Flaps ...... Airspeed....... Section 5 Performance Data Full Throttle .Per Placard 100% (DN) .Best Rate of Climb • Note ⚫ ° Balked Landing Climb Gradients shown are the gain in altitude for the horizontal distance traversed expressed as Feet per Nautical Mile. For operation in air colder than this table provides, use coldest data shown. For operation in air warmer than this table provides, use caution. This chart is required data for certification. However, significantly better performance can be achieved by climbing at Best Rate of Climb speeds shown with flaps down or following the Go-Around / Balked Landing procedure in Section 4. Weight Press Climb Alt Speed CLIMB GRADIENT - Feet/Nautical Mile Temperature °C LB FT KIAS 20 0 20 40 50 ISA SL 78 695 606 526 454 421 546 2000 78 559 479 407 341 310 438 4000 78 433 361 295 235 207 337 3150 6000 78 317 250 190 136 110 241 8000 78 209 148 93 43 19 151 10000 78 108 52 2 44 65 66 SL 78 940 831 733 644 603 756 2000 78 773 675 586 506 469 625 4000 78 619 530 450 377 343 501 2600 6000 78 477 396 323 257 226 385 8000 78 345 271 204 144 116 275 10000 78 223 155 94 39 13 172 P/N 11934-005 Original Issue 5-27 1 Section 5 Performance Data Balked Landing Rate of Climb Conditions: ⚫ Power ⚫ Mixture...... • Flaps........... ་ Climb Airspeed Cirrus Design SR20 Full Throttle Per Placard 100% (DN) .Noted • Note ⚫ Balked Landing Rate of Climb values shown are the full flaps change in altitude for unit time expended expressed in Feet per Minute. Blank shaded cells in the table represent performance below the minimum balked landing climb requirements. For operation in air colder than this table provides, use coldest data shown. For operation in air warmer than this table provides, use caution. This chart is required data for certification. However, significantly better performance can be achieved by climbing at Best Rate of Climb speeds shown with flaps down or following the Go-Around / Balked Landing procedure in Section 4. Weight Press Climb Alt Speed RATE OF CLIMB - Feet per Minute Temperature ~*C LB FT KIAS -20 0 20 40 50 ISA SL 78 840 763 687 613 577 706 2000 ☐ 78 703 626 551 478 442 584 4000 78 566 490 415 342 306 463 3150 6000 78 430 353 278 205 169 342 8000 78 295 217 141 67 31 221 10000 78 159 80 3 -72 108 99 SL 78 1130 1040 953 867 825 974 2000 78 968 879 792 708 667 831 4000 78 806 718 632 548 507 688 2600 6000 78 646 558 472 387 346 545 8000 78 487 398 311 226 184 402 10000 78 328 237 149 63 21 259 5-28 P/N 11934-005 Original Issue Cirrus Design SR20 Landing Distance Conditions: ⚫ Winds.. Runway. Flaps. • Power.... Section 5 Performance Data Zero .Dry, Level, Paved 100%, 50%, or 0% .3° Power Approach to 50 FT obstacle, then reduce power passing the estimated 50 foot point and smoothly continue power reduction to reach idle just prior to touchdown. 1° จ Note* The following factors are to be applied to the computed landing distance for the noted condition: " • Headwind - Subtract 10% from table distances for each 13 knots headwind. Tailwind - Add 10% to table distances for each 2 knots tailwind up to 10 knots. Grass Runway, Dry - Add 20% to ground roll distance. Grass Runway, Wet - Add 60% to ground roll distance. Sloped Runway - Increase table distances by 27% of the ground roll distance for each 1% of downslope. Decrease table distances by 9% of the ground roll distance for each 1% of upslope. " • Note • The above corrections for runway slope are required to be included herein. These corrections should be used with caution since published runway slope data is usually the net slope from one end of the runway to the other. Many runways will have portions of their length at greater or lesser slopes than the published slope, lengthening (or shortening) landing ground roll estimated from the table. ⚫ For operation in outside air temperatures colder than this table provides, use coldest data shown. * For operation in outside air temperatures warmer than this table provides, use caution. P/N 11934-005 Original Issue 5-29