V-speeds, cruise performance, fuel, and weights, digitized from the POH for planning and study.
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In the FlightDecide app since 2026-07-16. Reviewed 2026-09-28. 5 of 6 tables from the handbook. Anything marked “Not yet verified against the handbook” comes from FlightDecide's earlier library and hasn't been checked against the printed page.
Piper PA-28-140 Cherokee preflight numbers at a glance: max gross weight 2150 lb, typical useful load 900 lb, 36 gal usable fuel, cruise up to about 113 KTAS (reference figure at 8000 ft, standard day). 5 of the 6 performance tables below are read from the published POH/AFM; treat the ones marked “Not yet verified against the handbook” as estimates. Use them for planning and study, and confirm against the POH for your specific serial number before flight.
Not yet verified against the handbook
| Engine | Lycoming O-320-E2A |
| Propeller | Sensenich 76EM8S5-0-62 |
| Max gross weight | 2150 lb |
| Empty weight (typical) | 1250 lb |
| Useful load (typical) | 900 lb |
| Usable fuel | 36 gal |
| Service ceiling | 12,700 ft |
Not yet verified against the handbook
Knots indicated (KIAS) unless the POH states otherwise. Speeds vary by model year and serial; the placarded speeds and your POH govern.
| Speed | Value | Meaning |
|---|---|---|
| VS0 | 48 kt | Stall, landing configuration |
| VS1 | 56 kt | Stall, clean configuration |
| VX | 64 kt | Best angle of climb |
| VY | 74 kt | Best rate of climb |
| VA | 112 kt | Design maneuvering speed (at max gross) |
| VFE | 100 kt | Max flaps extended |
| VNO | 122 kt | Max structural cruising |
| VNE | 149 kt | Never exceed |
| Best glide | 72 kt | Best glide speed |
Not yet verified against the handbook
Source not verified: the library's record cites no handbook page for these rows. True airspeed and fuel flow depend on altitude, power setting, temperature, and leaning technique.
| Pressure alt (ft) | RPM | TAS (kt) | Fuel (GPH) |
|---|---|---|---|
| 2000 | 2100 | 86 | 6.4 |
| 2000 | 2400 | 101 | 8.2 |
| 2000 | 2600 | 109 | 9.7 |
| 4000 | 2100 | 88 | 6.2 |
| 4000 | 2400 | 102 | 8 |
| 4000 | 2600 | 110 | 9.4 |
| 6000 | 2100 | 90 | 6 |
| 6000 | 2400 | 103 | 7.8 |
| 6000 | 2600 | 111 | 9.1 |
| 8000 | 2100 | 90 | 5.8 |
| 8000 | 2400 | 105 | 7.6 |
| 8000 | 2600 | 113 | 8.9 |
Standard-day (ISA) rows shown, sampled across the POH table for readability; the FlightDecide app carries the full digitized table, including non-standard temperatures.
Figures read off the handbook's charts at 2150 lb, 0 ft pressure altitude, 20 °C. Real-world technique, wind, surface, and density altitude move these substantially, so apply your own margin (many pilots use 1.5× the book number) and run the numbers for the actual conditions.
| From the handbook | Distance |
|---|---|
| Takeoff ground roll | 880 ft |
| Takeoff over a 50 ft obstacle | 1850 ft |
| Landing ground roll | 540 ft |
| Landing over a 50 ft obstacle | 1090 ft |
| Rate of climb | 595 fpm |
See how density altitude stretches these distances on a hot day.
TAKEOFF PERFORMANCE. FLAPS 0 deg. PAVED LEVEL DRY RUNWAY. FULL POWER BEFORE BRAKE RELEASE. ZERO WIND. EXTRAPOLATION OF CHART ABOVE 7000 FT. IS INVALID. GROSS WEIGHT: 1950 LBS. (solid curves) / 2150 LBS. (dashed curves). AIRSPEED THROUGH 50 FEET: 1950 LBS. - 72 MPH CAS; 2150 LBS. - 76 MPH CAS. NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING INSTALLATION ON PERFORMANCE. Axes: DENSITY ALTITUDE - FEET (0 to 7000) against TAKE-OFF DISTANCE - FEET (500 to 4000). GROUND ROLL and OVER 50 FT. are separate labelled curves, each drawn twice, once per weight; only the 2150 lb (dashed) pair was read. The sheet is plotted against DENSITY altitude and carries no temperature axis, so each cell here is the chart read at the density altitude its pressure altitude and OAT give. This sheet is plotted against DENSITY altitude and has no temperature axis; each figure here is the chart read at the density altitude that pressure altitude and temperature give.
Source: Pilot's Operating Manual, Piper PA-28-140 Cherokee Cruiser, incorporating FAA Approved Airplane Flight Manual Report VB-557 (FAA approved 14 May 1973); performance charts issued 6 July 1973, revised 13 June 1974 · Takeoff
| Pressure altitude | 0 °C | 10 °C | 20 °C | 30 °C | 40 °C |
|---|---|---|---|---|---|
| Sea level | 755 / 1,615 | 880 / 1,850 | 1,030 / 2,110 | 1,190 / 2,410 | |
| 1,000 ft | 897 / 1,875 | 1,040 / 2,130 | 1,200 / 2,420 | 1,350 / 2,760 | |
| 2,000 ft | 1,055 / 2,144 | 1,200 / 2,435 | 1,360 / 2,770 | 1,515 / 3,165 | |
| 3,000 ft | 1,240 / 2,441 | 1,370 / 2,785 | 1,520 / 3,180 | 1,670 / 3,640 | |
| 4,000 ft | 1,483 / 2,779 | 1,569 / 3,183 | 1,694 / 3,646 | 1,831 / 4,184 |
| Pressure altitude | 0 °C | 10 °C | 20 °C | 30 °C | 40 °C |
|---|---|---|---|---|---|
| Sea level | 662 / 1,388 | 785 / 1,620 | 930 / 1,875 | 1,070 / 2,140 | |
| 1,000 ft | 796 / 1,650 | 930 / 1,885 | 1,070 / 2,150 | 1,210 / 2,430 | |
| 2,000 ft | 953 / 1,905 | 1,080 / 2,160 | 1,220 / 2,445 | 1,360 / 2,785 | |
| 3,000 ft | 1,096 / 2,156 | 1,225 / 2,455 | 1,365 / 2,800 | 1,505 / 3,220 | |
| 4,000 ft | 1,261 / 2,438 | 1,390 / 2,797 | 1,517 / 3,210 | 1,667 / 3,734 |
read from the handbook's chart extrapolated beyond the handbook
This handbook publishes performance as charts, not tables. Two people read these figures off its curves, independently, and they are shown only where the readings agreed, so they are close to what the chart shows rather than exact, within about 25 ft. Reading the chart's own worked example back from them comes out 10 ft from the answer it prints.
LANDING PERFORMANCE. GROSS WEIGHT 2150 LBS. PAVED LEVEL DRY RUNWAY. POWER OFF. 40 deg FLAPS. ZERO WIND. MAXIMUM BRAKING. APPROACH AIRSPEED 71 MPH CAS. NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING INSTALLATION ON PERFORMANCE. Axes: DENSITY ALTITUDE, FEET (0 to 7000) against LANDING DISTANCE, FEET (200 to 1400). One weight only; GROUND ROLL and OVER 50 FT. are two labelled solid curves. Plotted against DENSITY altitude with no temperature axis. This sheet is plotted against DENSITY altitude and has no temperature axis; each figure here is the chart read at the density altitude that pressure altitude and temperature give.
Source: Pilot's Operating Manual, Piper PA-28-140 Cherokee Cruiser, incorporating FAA Approved Airplane Flight Manual Report VB-557 (FAA approved 14 May 1973); performance charts issued 6 July 1973, revised 13 June 1974 · Landing
| Pressure altitude | 0 °C | 10 °C | 20 °C | 30 °C | 40 °C |
|---|---|---|---|---|---|
| Sea level | 511 / 1,051 | 540 / 1,090 | 565 / 1,125 | 585 / 1,160 | |
| 1,000 ft | 546 / 1,096 | 565 / 1,125 | 590 / 1,160 | 610 / 1,190 | |
| 2,000 ft | 570 / 1,121 | 590 / 1,160 | 610 / 1,195 | 630 / 1,230 | |
| 3,000 ft | 590 / 1,180 | 610 / 1,200 | 630 / 1,230 | 650 / 1,270 | |
| 4,000 ft | 611 / 1,242 | 631 / 1,241 | 650 / 1,271 | 670 / 1,311 |
read from the handbook's chart extrapolated beyond the handbook
This handbook publishes performance as charts, not tables. Two people read these figures off its curves, independently, and they are shown only where the readings agreed, so they are close to what the chart shows rather than exact, within about 25 ft. Reading the chart's own worked example back from them comes out 10 ft from the answer it prints.
CLIMB PERFORMANCE. TAKEOFF GROSS WEIGHT 2150 LBS. FLAPS 0 deg. POWER - FULL THROTTLE. MIXTURE - LEAN PER LYCOMING INSTRUCTIONS. 89 MPH CAS. NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING INSTALLATION ON PERFORMANCE. Axes: DENSITY ALTITUDE-FEET (0 to 14000) against RATE OF CLIMB-FEET PER MINUTE (0 to 1400, labelled every 200). A single line; no temperature axis. The drawn line stops at about 20 fpm / 12,900 ft density altitude and does not reach the axis. This sheet is plotted against DENSITY altitude and has no temperature axis; each figure here is the chart read at the density altitude that pressure altitude and temperature give.
Source: Pilot's Operating Manual, Piper PA-28-140 Cherokee Cruiser, incorporating FAA Approved Airplane Flight Manual Report VB-557 (FAA approved 14 May 1973); performance charts issued 6 July 1973, revised 13 June 1974 · Climb
| Pressure altitude | -20 °C | 0 °C | 20 °C | 40 °C |
|---|---|---|---|---|
| Sea level | 595 | 490 | ||
| 1,000 ft | 540 | 430 | ||
| 2,000 ft | 480 | 370 | ||
| 3,000 ft | 430 | 320 | ||
| 4,000 ft | 380 | 270 |
read from the handbook's chart extrapolated beyond the handbook
This handbook publishes performance as charts, not tables. Two people read these figures off its curves, independently, and they are shown only where the readings agreed, so they are close to what the chart shows rather than exact, within about 25 fpm. Reading the chart's own worked example back from them comes out 11 fpm from the answer it prints.
Common QuestionsPer the library's cruise table, not yet verified against the handbook, up to about 113 KTAS at 8000 ft on a standard day, burning roughly 8.9 GPH at that setting. Typical everyday cruise settings run slower and leaner; see the table above.
36 gallons usable. At a high-cruise burn of 8.9 GPH that is roughly 4.0 hours to dry tanks. Plan with reserves, never to zero.
About 900 lb for a typically equipped example (2150 lb max gross minus a typical empty weight of 1250 lb). Your aircraft's actual empty weight and CG come from its own weight-and-balance records. Always use those, not type averages.
VNE (never exceed) is 149 kt and VNO (max structural cruising) is 122 kt. Full V-speed table above; verify against the POH for your serial.
Check today's wind against your personal crosswind maximum.
See what heat and elevation do to these takeoff and climb numbers.
Fold these numbers into a structured preflight decision.
FlightDecide ships this aircraft as a built-in profile: it computes your fuel, weight and balance, and takeoff/landing performance for the actual conditions, scores 8 risk categories against your personal minimums, and explains the result in plain language.
Get FlightDecide on the App StoreReference data for planning and study: approximate, and not a substitute for the FAA-approved AFM/POH for your specific aircraft, an official weather briefing, or your judgment as pilot in command (14 CFR 91.3). Source: PA-28-140 Cherokee Owner's Handbook, Piper Aircraft Corporation Data synced from the FlightDecide aircraft library on 2026-09-28.