Performance Data for Cessna 152
Cessna 152 · Performance Data
Overview
The Cessna Model 152 is a two-seat, single-engine aircraft that is widely recognized for its reliability and ease of handling, making it a popular choice for flight training and personal use. This performance section provides essential data derived from actual flight tests, enabling pilots to plan flights with accuracy under various conditions. The charts and tables included cover critical performance metrics such as takeoff distances, climb rates, cruise performance, and fuel requirements, all of which are vital for safe and efficient flight operations. The data is based on standard conditions and average piloting techniques, with notes on how to adjust for different variables such as altitude, temperature, and wind conditions.
- Performance data is based on actual flight tests and average piloting techniques.
- Takeoff distances can be affected by altitude, temperature, and wind conditions.
- Cruise performance varies with power settings and altitude, impacting fuel consumption and range.
- Landing distances should consider field conditions and wind adjustments.
Document
Source
Originally published by www.firebirdcreative.services. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Performance Data
- Pages
- 19
- File size
- 6.3 MB
- Publisher
- www.firebirdcreative.services
Specifications & performance
Extracted from this document.
Specifications
- Range (nm)
- 265
- Engine (hp)
- 110
- Length (ft)
- 27
- Propeller
- fixed
- Wingspan (ft)
- 36
- Engine model
- Lycoming O-235-L2C
- Max speed (kt)
- 99
- Cruise speed (kt)
- 99
- Empty weight (lb)
- 1,610
- Fuel capacity (gal)
- 24.5
- Rate of climb (fpm)
- 720
- Service ceiling (ft)
- 12,000
- Max takeoff weight (lb)
- 1,670
Performance
- Fuel burn (gph)
- 5.2
- Landing over 50ft
- 1,300
- Max crosswind (kt)
- 12
- Takeoff over 50ft
- 1,820
- Landing distance (ft)
- 535
- Takeoff distance (ft)
- 980
- Stall speed clean (kt)
- 36
- Stall speed landing (kt)
- 36
V-speeds
- VA
- 40
- VR
- 50
- VX
- 60
- VY
- 70
- VS1
- 36
- VSO
- 36
Weight & balance
- Useful load (lb)
- 60
- Max ramp weight (lb)
- 1,670
- Basic empty weight (lb)
- 1,610
- Max landing weight (lb)
- 1,670
- Max takeoff weight (lb)
- 1,670
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In this document
Introduction
Performance data charts on the following pages are presented so that you may know what to expect from the airplane under various conditions, and also, to facilitate the planning of flights in detail and with reasonable accuracy. The data in the charts has been computed from actual flight tests with the airplane and engine in good condition and using average piloting techniques.
Takeoff Performance
For a takeoff weight of 1610 pounds at a pressure altitude of 1500 feet and a temperature of 28°C, the ground roll is 980 feet, and the total distance to clear a 50-foot obstacle is 1820 feet. Adjustments for wind conditions can reduce these distances.
Cruise Performance
Cruising at 6000 feet with a power setting of approximately 65% results in a true airspeed of 99 knots and a fuel flow of 5.2 gallons per hour. The total fuel requirement for a flight of 265 nautical miles is estimated at 21.0 gallons, including reserves.
Landing Performance
Landing distances for a field altitude of 2000 feet and a temperature of 25°C are 535 feet for ground roll and 1300 feet to clear a 50-foot obstacle. Adjustments for wind can also be applied to these figures.
Safety notes
- Ensure to lean the mixture for maximum RPM during takeoff and climb above 3000 feet.
- Consider the effects of temperature on climb performance, increasing time and fuel estimates by 10% for every 10°C above standard.
Full document text
CESSNA MODEL 152 SECTION 5 PERFORMANCE SECTION 5 PERFORMANCE TABLE OF CONTENTS Page Introduction Use of Performance Charts Sample Problem Takeoff Cruise Fuel Required Landing Demonstrated Operating Temperature Figure 5-1, Airspeed Calibration Figure 5-2, Temperature Conversion Chart Figure 5-3, Stall Speeds Figure 5-4, Wind Components 5-3 5-3 5-3 • 5-4 • 5-5 • 5-5 5-7 • 5-7 5-8 • 5-9 • 5-10 5-11 Figure 5-5, Takeoff Distance 5-12 Figure 5-6, Maximum Rate Of Climb Figure 5-7, Time, Fuel, And Distance To Climb Figure 5-8, Cruise Performance Figure 5-9, Range Profile - 24.5 Gallons Fuel Range Profile - 37.5 Gallons Fuel 5-13 5-14 5-15 5-16 5-17 Figure 5-10, Endurance Profile - 24.5 Gallons Fuel Endurance Profile - 37.5 Gallons Fuel 5-18 5-19 Figure 5-11, Landing Distance 5-20 20 April 1981 5-1/(5-2 blank) CESSNA MODEL 152 SECTION 5 PERFORMANCE INTRODUCTION Performance data charts on the following pages are presented so that you may know what to expect from the airplane under various conditions, and also, to facilitate the planning of flights in detail and with reasonable accuracy. The data in the charts has been computed from actual flight tests with the airplane and engine in good condition and using average piloting techniques. It should be noted that the performance information presented in the range and endurance profile charts allows for 45 minutes reserve fuel at the specified cruise power. Fuel flow data for cruise is based on the recommended lean mixture setting. Some indeterminate variables such as mixture leaning technique, fuel metering characteristics, engine and propeller condition, and air turbulence may account for variations of 10% or more in range and endurance. Therefore, it is important to utilize all available information to estimate the fuel required for the particular flight. USE OF PERFORMANCE CHARTS Performance data is presented in tabular or graphical form to illus- trate the effect of different variables. Sufficiently detailed information is provided in the tables so that conservative values can be selected and used to determine the particular performance figure with reasonable accuracy. SAMPLE PROBLEM The following sample flight problem utilizes information from the various charts to determine the predicted performance data for a typical flight. The following information is known: AIRPLANE CONFIGURATION Takeoff weight Usable fuel TAKEOFF CONDITIONS Field pressure altitude Temperature Wind component along runway Field length 20 April 1981 1610 Pounds 24.5 Gallons 1500 Feet 28°C (16°C above standard) 12 Knot Headwind 3500 Feet 5-3 SECTION 5 PERFORMANCE CESSNA MODEL 152 CRUISE CONDITIONS Total distance Pressure altitude Temperature Expected wind enroute LANDING CONDITIONS Field pressure altitude Temperature Field length TAKEOFF 265 Nautical Miles 5500 Feet 20°C (16°C above standard) 10 Knot Headwind 2000 Feet 25°C 3000 Feet The takeoff distance chart, figure 5-5, should be consulted, keeping in mind that the distances shown are based on the short field technique. Conservative distances can be established by reading the chart at the next higher value of altitude and temperature. For example, in this particular sample problem, the takeoff distance information presented for a pressure altitude of 2000 feet and a temperature of 30°C should be used and results in the following: Ground roll Total distance to clear a 50-foot obstacle 980 Feet 1820 Feet These distances are well within the available takeoff field length. Howev- er, a correction for the effect of wind may be made based on Note 3 of the takeoff chart. The correction for a 12 knot headwind is: 12 Knots 9 Knots × 10% = 13% Decrease This results in the following distances, corrected for wind: 5-4 Ground roll, zero wind Decrease in ground roll (980 feet × 13%) Corrected ground roll Total distance to clear a 50-foot obstacle, zero wind Decrease in total distance 980 127 853 Feet 1820 237 (1820 feet × 13%) Corrected total distance to clear 50-foot obstacle 1583 Feet 20 April 1981 CESSNA MODEL 152 SECTION 5 PERFORMANCE CRUISE The cruising altitude should be selected based on a consideration of trip length, winds aloft, and the airplane's performance. A typical cruising altitude and the expected wind enroute have been given for this sample problem. However, the power setting selection for cruise must be deter- mined based on several considerations. These include the cruise perfor- mance characteristics presented in figure 5-8, the range profile chart presented in figure 5-9, and the endurance profile chart presented in figure 5-10. The relationship between power and range is illustrated by the range profile chart. Considerable fuel savings and longer range result when lower power settings are used. For this sample problem, a cruise power of approximately 65% will be used. The cruise performance chart, figure 5-8, is entered at 6000 feet altitude and 20°C above standard temperature. These values most nearly corres- pond to the planned altitude and expected temperature conditions. The engine speed chosen is 2400 RPM, which results in the following: Power True airspeed Cruise fuel flow 64% 99 Knots 5.2 GPH The power computer may be used to determine power and fuel consump- tion more accurately during the flight. FUEL REQUIRED The total fuel requirement for the flight may be estimated using the performance information in figures 5-7 and 5-8. For this sample problem, figure 5-7 shows that a climb from 2000 feet to 6000 feet requires 1 gallon of fuel. The corresponding distance during the climb is 9 nautical miles. These values are for a standard temperature and are sufficiently accurate for most flight planning purposes. However, a further correction for the effect of temperature may be made as noted on the climb chart. The approximate effect of a non-standard temperature is to increase the time, fuel, and distance by 10% for each 10°C above standard temperature, due to
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the lower rate of climb. In this case, assuming a temperature 16°C above standard, the correction would be: 20 April 1981 16°C 10°C × 10% = 16% Increase 5-5 SECTION 5 PERFORMANCE CESSNA MODEL 152 With this factor included, the fuel estimate would be calculated as follows: Fuel to climb, standard temperature Increase due to non-standard temperature (1.0 × 16%) Corrected fuel to climb 1.0 0.2 1.2 Gallons Using a similar procedure for the distance to climb results in 10 nautical miles. The resultant cruise distance is: Total distance Climb distance Cruise distance 265 -10 255 Nautical Miles With an expected 10 knot headwind, the ground speed for cruise is predicted to be: 99 -10 89 Knots Therefore, the time required for the cruise portion of the trip is: 255 Nautical Miles = 2.9 Hours 89 Knots The fuel required for cruise is: 2.9 hours 5.2 gallons/hour = 15.1 Gallons A 45-minute reserve requires: 45 60 * 5.2 gallons/hour = 3.9 Gallons The total estimated fuel required is as follows: Engine start, taxi, and takeoff 5-6 Climb Cruise Reserve Total fuel required 0.8 1.2 15.1 3.9 21.0 Gallons 20 April 1981 CESSNA MODEL 152 SECTION 5 PERFORMANCE Once the flight is underway, ground speed checks will provide a more accurate basis for estimating the time enroute and the corresponding fuel required to complete the trip with ample reserve. LANDING A procedure similar to takeoff should be used for estimating the landing distance at the destination airport. Figure 5-11 presents landing distances for various airport altitude and temperature combinations using the short field technique. The distances corresponding to 2000 feet and 30°C are as follows: Ground roll Total distance to clear a 50-foot obstacle 535 Feet 1300 Feet A correction for the effect of wind may be made based on Note 2 of the landing chart using the same procedure as outlined for takeoff. DEMONSTRATED OPERATING TEMPERATURE Satisfactory engine cooling has been demonstrated for this airplane with an outside air temperature 23°C above standard. This is not to be considered as an operating limitation. Reference should be made to Section 2 for engine operating limitations. 20 April 1981 5-7 SECTION 5 PERFORMANCE AIRSPEED CALIBRATION CESSNA MODEL 152 CONDITIONS: Power required for level flight or maximum rated RPM dive. FLAPS UP KIAS 40 KCAS 46 449 5550 50 60 53 60 28 66 70 80 90 100 110 120 130 140 69 78 88 97 107 117 127 136 FLAPS 10º KIAS KCAS 444 40 559 50 60 52 61 770 6859 80 85 70 80 84 FLAPS 30° KIAS KCAS 475 40 50 60 43 51 61 71 77 70 888 80 82 8 899 85 87 Figure 5-1. Airspeed Calibration 5-8 20 April 1981 CESSNA MODEL 152 SECTION 5 PERFORMANCE TEMPERATURE CONVERSION CHART 120 100 80 60 60 DEGREES FAHRENHEIT 40 40 20 20 -20 -40 -40 -20 0 20 40 60 60 20 April 1981 DEGREES CELSIUS Figure 5-2. Temperature Conversion Chart 5-9 SECTION 5 PERFORMANCE CESSNA MODEL 152 STALL SPEEDS CONDITIONS: Power Off NOTES: 1. 2. Altitude loss during a stall recovery may be as much as 160 feet. KIAS values are approximate and are based on airspeed calibration data with power off. MOST REARWARD CENTER OF GRAVITY ANGLE OF BANK WEIGHT LBS FLAP DEFLECTION 00 30° 45° 60° KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 36 36 46 39 49 1670 10º 36 43 39 39 46 30° 31 41 33 44 w to t 43 55 51 65 5 43 51 51 19 61 37 49 49 44 58 888 MOST FORWARD CENTER OF GRAVITY WEIGHT LBS FLAP DEFLECTION 0° ANGLE OF BANK 30° 45° 60° KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 40 48 48 43 33 52 48 1670 10° 40 46 43 49 48 30° 35 43 38 46 46 42 5-10 57 557 55 59 57 555 57 57 68 99 88 65 555 51 49 61 19 Figure 5-3. Stall Speeds 20 April 1981 JJ J 20 April 1981 CESSNA MODEL 152 WIND COMPONENTS NOTE: Maximum demonstrated crosswind velocity is 12 knots (not a limitation). 25 30 30 WIND VELOCITY - KNOTS 30- 15 20 20 ANGLE BETWEEN WIND DIRECTION AND RUNWAY -15- -20- 10°. 20° 30°. 40° 10 TAILWIND WIND COMPONENT KNOTS HEADWIND 10 0 0 LO 5 10 50° 60°. 70°. 80°. 90°, 100°. 160º. 1400 5 120°. 10 15 20 25 CROSSWIND COMPONENT - KNOTS Figure 5-4. Wind Components 30 30 5-11 SECTION 5 PERFORMANCE PERFORMANCE SECTION 5 5-12 512 CONDITIONS: Flaps 10° Full Throttle Prior to Brake Release Paved, Level, Dry Runway Zero Wind NOTES: 1. 2. 3. 4. TAKEOFF DISTANCE Short field technique as specified in Section 4. SHORT FIELD Prior to takeoff from fields above 3000 feet elevation, the mixture should be leaned to give maximum RPM in a full throttle, static runup. Decrease distances 10% for each 9 knots headwind. For operation with tailwinds up to 10 knots, increase distances by 10% for each 2 knots. For operation on a dry, grass runway, increase distances by 15% of the "ground roll" figure. TAKEOFF 0°C 10°C 20°C 30°C 40°C WEIGHT LBS SPEED PRESS KIAS ALT TOTAL TOTAL TOTAL TOTAL TOTAL 1670 LIFT AT OFF 50 FT 50 54 FT GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR GRND TO CLEAR ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS ROLL 50 FT OBS S.L. 640 1190 695 1290 755 1390 810 1495 875 1605 1000 705 1310 765 1420 825 1530 890 1645 960 1770 2000 775 1445 840 1565 910 1690 980 1820 1055 1960 3000 855 1600 925 1730 1000 1870 1080 2020 1165 2185 4000 940 1775 1020 1920 1100 2080 1190 2250 1285 2440 5000 1040 1970 1125 2140 1215 2320 1315 2525 1420 2750 6000 1145 2200 1245 2395 1345 2610 1455 2855 1570 3125 7000 1270 2470 1375 2705 1490 2960 1615 3255 1745 3590 8000 1405 2800 1525 3080 1655 3395 1795 3765 1940 4195 20 April 1981 Figure 5-5. Takeoff Distance MODEL 152 CESSNA CESSNA MODEL 152 SECTION 5 PERFORMANCE MAXIMUM RATE OF CLIMB CONDITIONS: Flaps Up Full Throttle NOTE: Mixture leaned above 3000 feet for maximum RPM. PRESS CLIMB RATE OF CLIMB - FPM WEIGHT ALT SPEED LBS FT KIAS -20°C 0°C 20°C 40°C 1670 S.L. 2000 4000 6000 8000 10,000 12,000 2238222 67 835 765 700 630 66 735 670 600 535 65 635 570 505 445 63 535 475 415 355 62 440 380 320 265 61 340 285 230 175 60 245 190 135 85 Figure 5-6. Maximum Rate of Climb 20 April 1981 5-13 SECTION 5 PERFORMANCE CESSNA MODEL 152 TIME, FUEL, AND DISTANCE TO CLIMB MAXIMUM RATE OF CLIMB CONDITIONS: Flaps Up Full Throttle Standard Temperature NOTES: 1. 2. 3. Add 0.8 of a gallon of fuel for engine start, taxi and takeoff allowance. Mixture leaned above 3000 feet for maximum RPM. Increase time, fuel and distance by 10% for each 10°C above standard temperature. 4. Distances shown are based on zero wind. J J J J J J FROM SEA LEVEL WEIGHT LBS PRESSURE ALTITUDE CLIMB TEMP SPEED RATE OF CLIMB ос TIME FUEL USED FT KIAS FPM MIN GALLONS DISTANCE NM 1670 S.L. 15 1000 2000 11 531 3000 9 4000 7 5000 5 6000 3 7000 1 8000 -1 9000 -3 10,000 - 5 11,000 -7 12,000 -9 2 2 2 3 3 3 3 22222 2 67 715 0 0 0 66 675 1 0.2 66 630 3 0.4 65 590 5 0.7 65 550 6 0.9 64 505 8 1.2 63 465 10 1.4 63 425 13 1.7 14 62 380 15 2.0 62 340 18 2.3 300 21 2.6 61 255 60 215 22 25 3.0 29 3.4 235722112223 29 34 5-14 Figure 5-7. Time, Fuel, and Distance to Climb 20 April 1981 CESSNA MODEL 152 THIS DATA APPLICABLE ONLY TO AIRPLANES WITH LYCOMING O-235-L2C ENGINE. FOR AIRPLANES WITH ENGINE MODIFIED TO O-235-N2C, REFER TO DATA IN SECTION 9 SUPPLEMENT CRUISE PERFORMANCE SECTION 5 PERFORMANCE CONDITIONS: 1670 Pounds Recommended Lean Mixture (See Section 4, Cruise) NOTE: Cruise speeds are shown for an airplane equipped with speed fairings which increase the speeds by approximately two knots. PRESSURE 20°C BELOW STANDARD TEMP STANDARD TEMPERATURE 20ºC ABOVE STANDARD TEMP ALTITUDE RPM FT % BHP % % KTAS GPH KTAS GPH KTAS GPH BHP BHP 2000 2400 2300 71 97 5.7 2200 62 92 5.1 2100 2000 49 4000 2450 2400 76 102 2300 67 2200 2100 2000 48 6000 2500 2400 2300 2200 57 2100 51 2000 46 29GON: 282221 22 55 87 4.5 81 4.1 6.1 96 5.4 60 91 4.8 53 86 4.4 81 3.9 72 101 64 8000 2550 2500 76 105 2400 2300 61 2200 2100 49 10,000 2500 72 105 2400 65 2300 2200 2100 48 12,000 2450 65 101 2400 62 2300 56 2200 51 2100 47 tag3G 28AAN 12%2 68 100 55 58 53 89 52222 222 223 2 5.8 96 5.2 90 4.6 85 4.2 80 3.8 6.2 5.5 95 5.0 90 4.5 84 4.1 5.8 99 5.3 61 94 4.7 4.3 51 83 4.0 5.3 99 5.0 93 4.6 88 4.2 49 82 3.9 45 PERRE F8652 26824 22 25654 62024 75 101 6.1 66 96 5.4 59 91 4.8 53 86 4.3 47 80 3.9 75 103 6.1 71 101 5.7 63 95 5.1 90 4.6 51 85 4.2 46 80 3.8 75 105 6.1 67 100 5.4 60 95 4.9 54 89 4.4 49 84 4.0 45 79 3.7 75 107 71 104 22 6.1 71 5.8 64 99 5.2 61 58 94 4.7 52 89 4.3 51 48 83 3.9 46 68 103 5.5 98 5.0 93 4.5 88 4.2 49 82 3.9 100 5.0 59 59 97 4.8 54 92 4.4 87 4.1 48 81 3.8 285 26844 8227 7655ES FENGE BENKI 70 101 63 56 51 46 70 67 100 60 54 49 45 71 104 64 57 52 48 44 106 103 64 103 62232 28221 222 22 5.7 95 5.1 90 4.6 85 4.2 79 3.8 5.7 5.4 95 4.9 89 4.4 84 4.0 78 3.7 5.7 99 5.2 94 4.7 88 4.3 83 3.9 77 3.6 5.7 5.4 98 4.9 93 4.5 87 4.2 82 3.8 5.2 58 97 4.8 53 92 4.4 86 4.0 45 81 3.8 99 4.8 56 96 4.6 52 91 4.3 85 4.0 44 79 3.7 Figure 5-8. Cruise Performance 20 April 1981 Revision 1 31 March 1983 5-15 5-16 SECTION 5 PERFORMANCE THIS DATA APPLICABLE ONLY TO AIRPLANES WITH LYCOMING 0-235-L2C ENGINE FOR AIRPLANES WITH ENGINE MODIFIED TO 0-235-N2C, REFER TO DATA IN SECTION 9 SUPPLEMENT RANGE PROFILE 45 MINUTES RESERVE 24.5 GALLONS USABLE FUEL CESSNA MODEL 152 CONDITIONS: 1670 Pounds Recommended Lean Mixture for Cruise Standard Temperature Zero Wind NOTES: 1. This chart allows for the fuel used for engine start, taxi, takeoff and climb, and the distance during climb. 2. Performance is shown for an airplane equipped with speed fairings which increase the cruise speeds by approximately two knots. ALTITUDE - FEET 12,000 10,000 FULL THROTTLE 8000 107 KTAS 6000 105 198 KTAS 4000 2000 S.L. 300 75% POWER 65% POWER 80 102 KTAS KTAS 94 KTAS KTAS 90 KTAS 79 72 KTAS 55% POWER 45% POWER 100 94 87 -77 [KTAS KTAS KTAST KTAS 350 400 RANGE NAUTICAL MILES 450 500 Figure 5-9. Range Profile (Sheet 1 of 2) Revision 1 20 April 1981 - 31 March 1983
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