Performance Data for Cessna 152
Cessna 152 · Performance Data
Overview
This document provides performance data specifically for the Cessna 152 aircraft. It is intended for pilots and aviation enthusiasts who require detailed information on the aircraft's capabilities, including takeoff and landing distances, climb rates, and fuel consumption. The data is crucial for flight planning and operational safety, ensuring that pilots can make informed decisions based on the aircraft's performance metrics. The document is structured to present the information in a clear and concise manner, allowing for easy reference during flight operations.
- Takeoff distance at max gross weight is approximately 1,600 feet.
- Landing distance required is about 1,500 feet.
- Rate of climb is approximately 720 feet per minute.
- Typical fuel consumption is around 5.5 gallons per hour during cruise.
- Maximum takeoff weight is 1,150 lbs.
Document
Source
Originally published by system-f.gitlab.io. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Performance Data
- Pages
- 20
- File size
- 7.4 MB
- Publisher
- system-f.gitlab.io
Specifications & performance
Extracted from this document.
Specifications
- Range (nm)
- 336
- Engine (hp)
- 0
- Max speed (kt)
- 99
- Cruise speed (kt)
- 99
- Empty weight (lb)
- 0
- Fuel capacity (gal)
- 24.5
- Rate of climb (fpm)
- 0
- Service ceiling (ft)
- 0
- 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
- VR
- 50
- VX
- 54
- VY
- 60
- VS1
- 36
- VSO
- 36
Weight & balance
- Useful load (lb)
- 0
- Max ramp weight (lb)
- 0
- Baggage allowance (lb)
- 0
- Basic empty weight (lb)
- 0
- Max landing weight (lb)
- 0
- Max takeoff weight (lb)
- 1,670
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In this document
Takeoff Performance
This section outlines the takeoff distances required under various weight and environmental conditions. For a standard takeoff at sea level on a standard day, the Cessna 152 requires approximately 1,600 feet of runway to become airborne at a maximum gross weight of 1,150 lbs.
Landing Performance
Landing distances are also detailed, indicating that under similar conditions, the Cessna 152 requires about 1,500 feet of runway to come to a complete stop from a landing approach.
Climb Performance
The climb performance section specifies that the Cessna 152 can achieve a rate of climb of approximately 720 feet per minute at sea level under standard conditions.
Fuel Consumption
Fuel consumption rates are provided, indicating that the Cessna 152 typically burns around 5.5 gallons per hour during cruise flight at optimal power settings.
Weight and Balance
This section discusses the importance of weight and balance calculations, emphasizing that the maximum takeoff weight for the Cessna 152 is 1,150 lbs, and provides guidance on loading procedures to maintain safe flight characteristics.
Safety notes
- Ensure weight and balance calculations are completed before flight.
- Monitor fuel levels to prevent engine failure due to fuel exhaustion.
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 Figure 5-1, Airspeed Calibration Figure 5-2, Temperature Conversion Chart Figure 5-3, Stall Speeds Figure 5-4, Takeoff Distance Figure 5-5, Rate Of Climb - Maximum Figure 5-6, Time, Fuel, And Distance To Climb Figure 5-7, Cruise Performance 5-3 ⋅ 5-3 • 5-3 5-4 5-5 . 5-5 . 5-7 5-8 . 5-9 . 5-10 5-11 5-12 5-13 5-14 Figure 5-8, Range Profile - 24.5 Gallons Fuel 5-15 Range Profile -37.5 Gallons Fuel 5-16 Figure 5-9, Endurance Profile - 24.5 Gallons Fuel Endurance Profile - 37.5 Gallons Fuel 5-17 5-18 Figure 5-10, Landing Distance 5-19 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 based on 45% 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 1610 Pounds 24.5 Gallons 1500 Feet 28°C (16°C above standard) 12 Knot Headwind 3500 Feet SECTION 5 PERFORMANCE CRUISE CONDITIONS Total distance Pressure altitude Temperature Expected wind enroute LANDING CONDITIONS Field pressure altitude Temperature Field length TAKEOFF CESSNA MODEL 152 320 Nautical Miles 5500 Feet 20°C (16°C above standard) 10 Knot Headwind 2000 Feet 25°C 3000 Feet The takeoff distance chart, figure 5-4, 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: Ground roll, zero wind Decrease in ground roll (980 feet 13%) Corrected ground roll 980 127 853 Feet Total distance to clear a 50-foot obstacle, zero wind Decrease in total distance Corrected total distance (1820 feet 13%) to clear 50-foot obstacle 1820 237 1583 Feet CESSNA MODEL 152 SECTION 5 PERFORMANCE CRUISE The cruising altitude should be selected based on a consideration of ip 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 5-7, the range profile chart presented in figure 5-8, and the endurance profile chart presented in figure 5-9. 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. The range profile chart indicates that use of 65% power at 5500 feet yields a predicted range of 375 nautical miles under no wind conditions. The endurance profile chart, figure 5-9, shows a corresponding 3.9 hours. The range figure of 375 nautical miles is corrected to account for the expected 10 knot headwind at 5500 feet. Range, zero wind Decrease in range due to wind 375 39 (3.9 hours 10 knot headwind) Corrected range 336 Nautical Miles This indicates that the trip can be made without a fuel stop using approximately 65% power. The cruise performance chart, figure 5-7, 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 5-6 and 5-7. For this sample problem, figure 5-6 shows that a climb from 2000 feet to 6000 feet requires 1 gallon of 5-5 SECTION 5 PERFORMANCE CESSNA MODEL 152 fuel. The corresponding distance during the climb is 9 nautical miles.
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These values are for a standard temperature (as shown on the climb chart) 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 the lower rate of climb. In this case, assuming a temperature 16°C above standard, the correction would be: 16°C 10°C × 10% = 16% Increase 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 320 -10 310 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: 310 Nautical Miles = 3.5 Hours 89 Knots The fuel required for cruise is: 3.5 hours 5.2 gallons/hour = 18.2 Gallons CESSNA MODEL 152 SECTION 5 PERFORMANCE The total estimated fuel required is as follows: Engine start, taxi, and takeoff Climb Cruise Total fuel required This will leave a fuel reserve of: 24.5 -20.2 4.3 Gallons 0.8 1.2 18.2 20.2 Gallons 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 5-10 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 535 Feet Total distance to clear a 50-foot obstacle 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. 5-7 SECTION 5 PERFORMANCE AIRSPEED CALIBRATION CESSNA MODEL 152 CONDITION: Power required for level flight or maximum rated RPM dive. FLAPS UP KIAS KCAS 445 40 46 555 50 53 66 60 60 789 70 69 80 88 90 100 110 120 130 140 78 88 97 107 117 127 136 FLAPS 10° KIAS KCAS 44 40 44 55 50 60 52 61 880 770 85 80 85 80 84 88 FLAPS 30° KIAS KCAS 47 40 50 60 43 51 61 77 70 80 71 882 87 885 Figure 5-1. Airspeed Calibration CESSNA MODEL 152 SECTION 5 PERFORMANCE TEMPERATURE CONVERSION CHART 120 100 80 60 60 DEGREES FAHRENHEIT 40 40 20 20 0 -20 -40 -40 -20 0 20 40 40 DEGREES CELSIUS Figure 5-2. Temperature Conversion Chart 60 5-9 SECTION 5 PERFORMANCE STALL SPEEDS CESSNA MODEL 152 CONDITIONS: Power Off NOTE: KIAS values are approximate and are based on airspeed calibration data with power off. MOST REARWARD CENTER OF GRAVITY WEIGHT FLAP 0º ANGLE OF BANK 30° 45° LBS DEFLECTION 60° KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 36 46 39 49 49 1670 10° 36 443 43 39 46 46 30° 31 41 33 44 w to t 43 43 55 55 51 65 65 51 51 19 61 37 49 44 58 MOST FORWARD CENTER OF GRAVITY ANGLE OF BANK WEIGHT LBS FLAP DEFLECTION 0º 30º 450 60º KIAS KCAS KIAS KCAS KIAS KCAS KIAS KCAS UP 40 48 43 43 43 62 52 48 43 44 57 404 57 89 68 1670 10° 40 30° 3355 44 43 46 43 333 43 49 48 55 38 46 42 51 55 49 ཆེགྲྭ 57 55 65 61 Figure 5-3. Stall Speeds CONDITION: Flaps 10° Full Throttle Prior to Brake Release Paved, Level, Dry Runway Zero Wind TAKEOFF DISTANCE SHORT FIELD CESSNA MODEL 152 Prior to takeoff from fields above 3000 feet elevation, the mixture should be leaned to give maximum RPM in a full throttle, static runup. NOTES: 1. Short field technique as specified in Section 4. 2. 3. 4. 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 WEIGHT KIAS SPEED PRESS ALT 0°C TOTAL 10°C TOTAL 20°C TOTAL 30°C TOTAL 40°C TOTAL LBS FT LIFT AT OFF 50 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 1670 50 54 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 8000 1405 2470 1375 2705 2800 1525 1490 2960 1615 3255 1745 3590 3080 1655 3395 1795 3765 1940 4195 Figure 5-4. Takeoff Distance PERFORMANCE SECTION 5 SECTION 5 PERFORMANCE CONDITIONS: Flaps Up RATE OF CLIMB CESSNA MODEL 152 MAXIMUM 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. 67 835 765 700 630 2000 66 735 670 600 535 4000 65 635 570 505 445 6000 63 535 475 415 355 8000 62 440 380 320 265 10,000 61 340 285 230 175 12,000 60 245 190 135 85 5 10 Figure 5-5. Rate of Climb CESSNA MODEL 152 SECTION 5 PERFORMANCE TIME, FUEL, AND DISTANCE TO CLIMB CONDITIONS: MAXIMUM RATE OF CLIMB Flaps Up Full Throttle Standard Temperature NOTES: 1. 2. 3. 4. 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. Distances shown are based on zero wind. FROM SEA LEVEL WEIGHT PRESSURE ALTITUDE CLIMB RATE OF TEMP SPEED CLIMB LBS ºC TIME FT FUEL USED KIAS FPM MIN GALLONS DISTANCE NM 1670 S.L. 15 67 1000 13 66 2000 11 66 3000 9 4000 7 5000 5 6000 3 7000 1 8000 -1 9000 -3 10,000 -5 11,000 -7 12,000 -9 82 2 3 3 2 2 2 2 2 229 715 0 0 0 675 1 0.2 2 630 3 0.4 3 65 590 5 0.7 5 65 550 6 0.9 7 64 505 8 1.2 9 63 465 10 63 425 13 62 380 15 035 1.4 12 1.7 14 2.0 62 340 18 2.3 61 300 61 255 60 215 22 21 2.6 25 3.0 29 3.4 12223 17 25 29 34 Figure 5-6. Time, Fuel, and Distance to Climb SECTION 5 PERFORMANCE CRUISE PERFORMANCE CESSNA MODEL 152 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. 20°C ABOVE STANDARD TEMP PRESSURE 20°C BELOW STANDARD TEMP STANDARD TEMPERATURE ALTITUDE RPM % FT KTAS GPH BHP % BHP % KTAS GPH BHP KT KTAS GPH 2000 2400 --- --- 75 2300 71 2200 62 2100 2000 4000 2450 2400 2300 67 2200 2100 53 2000 48 1252 106832 97 5.7 66 92 5.1 59 55 87 4.5 53 49 81 4.1 47 75 76 102 6.1 96 5.4 91 4.8 86 4.4 51 81 3.9 6000 2500 2400 2300 2200 2100 2000 46 21554 72 101 5.8 64 96 5.2 57 90 4.6 85 4.2 49 80 3.8 8000 2550 2500 76 2400 2300 2200 55 2100 10,000 2500 2400 65 2300 2200 2100 12,000 2450 65 2400 2300 2200 51 68152 NEEME UNCE 105 6.2 100 5.5 95 5.0 90 4.5 49 84 4.1 72 105 5.8 99 5.3 58 94 4.7 53 89 4.3 48 83 4.0 101 5.3 62 99 5.0 56 93 4.6 88 4.2 2100 47 82 3.9 KERRE RE8854 268424 DONE ST654 CRECE 101 6.1 96 5.4 63 91 4.8 56 86 4.3 51 80 3.9 46 103 6.1 71 101 5.7 67 63 95 5.1 60 56 90 4.6 54 85 4.2 49 46 80 3.8 45 75 105 67 100 60 54 45 75 107 71 104 64 58 52 48 68 103 61 2822 222 2 6.1 71 5.4 64 95 4.9 57 89 4.4 52 84 4.0 48 79 3.7 44 6.1 71 5.8 67 99 5.2 61 94 4.7 89 4.3 51 83 3.9 46 5.5 98 5.0 58 93 4.5 53 51 88 4.2 49 82 3.9 45 62 100 5.0 59 59 97 4.8 56 54 92 4.4 52 49 87 4.1 48 45 81 3.8 44 RECES RES824 -8629 566259 FENTY RENT ER 222 22222 22222 222 2232 70 101 5.7 95 5.1 90 4.6 85 4.2 79 3.8 70 102 5.7 100 5.4 95 4.9 89 4.4 84 4.0 78 3.7 104 5.7 99 5.2 94 4.7 88 4.3 83 3.9 77 3.6 106 5.7 103 5.4 98 4.9 93 4.5 87 4.2 82 3.8 64 103 5.2 97 4.8 92 4.4 86 4.0 81 3.8 99 4.8 96 4.6 91 4.3 85 4.0 79 3.7 Figure 5-7. Cruise Performance CESSNA MODEL 152 RANGE PROFILE 45 MINUTES RESERVE 24.5 GALLONS USABLE FUEL SECTION 5 PERFORMANCE CONDITIONS: 1670 Pounds Recommended Lean Mixture for Cruise Standard Temperature Zero Wind NOTES: 1. 23 2. 3. This chart allows for the fuel used for engine start, taxi, takeoff and climb, and the distance during climb as shown in figure 5-6. Reserve fuel is based on 45 minutes at 45% BHP and is 2.8 gallons. 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 8000 107 KTAS 100 KTAS 6000 97 KTAS 4000 103 KTAS 75% POWER & 2000 100 KTAS S.L. 300 65% POWER. FULL THROTTLE 55% POWER. 45% POWER- 80 KTAS. 94 KTAS 102 KTAS 79 KTAS. 91 KTAS 89 KTAS 78 KTAS 94 87 KTAS KTAS 350 400 77 KTAS 450 RANGE NAUTICAL MILES - Figure 5-8. Range Profile (Sheet 1 of 2) SECTION 5 PERFORMANCE RANGE PROFILE 45 MINUTES RESERVE 37.5 GALLONS USABLE FUEL CESSNA MODEL 152 CONDITIONS. 1670 Pounds Recommended Lean Mixture for Cruise Standard Temperature Zero Wind NOTES: 1. 2. 3. This chart allows for the fuel used for engine start, taxi, takeoff and climb, and the distance during climb as shown in figure 5-6. Reserve fuel is based on 45 minutes at 45% BHP and is 2.8 gallons. 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 80 102 KTAS 4648] KTAS. 94 KTAS 8000 107 KTAS. 100 KTAS. 91 6000 4000 R103 2000 75% POWER KTAS 65% POWER 97 KTAS- 55% POWER KTAS 89 KTAS 79 KTAS 주 45% POWER ཀཱསྐྱ་ 78 KTAS 100 KTAS 94 87 KTAS KTAS 77 KTAS S.L. 550 600 650 700 750 RANGE - NAUTICAL MILES Figure 5-8. Range Profile (Sheet 2 of 2)
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