Performance Data for the Piper PA-11 Cub Special
Piper PA-11 Cub Special · Performance Data
Overview
This document provides performance data specifically for the Piper PA-11 Cub Special. It is intended for pilots and aviation enthusiasts who require detailed information regarding the aircraft's capabilities. The data includes essential performance metrics such as takeoff distances, climb rates, and fuel consumption under various conditions. This information is crucial for flight planning and operational safety, ensuring that pilots can make informed decisions based on the aircraft's performance characteristics.
- Takeoff distance at max weight is approximately 1,200 feet.
- Rate of climb at max weight is about 600 feet per minute.
- Cruise speed is around 70 knots at 75% power.
- Fuel consumption in cruise is about 5.5 gallons per hour.
- Landing distance at max weight is approximately 1,000 feet.
Document
Source
Originally published by aerowoodaviation.com. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Performance Data
- Pages
- 31
- File size
- 6.1 MB
- Publisher
- aerowoodaviation.com
Specifications & performance
Extracted from this document.
Specifications
- Cruise speed (kt)
- 142
- Empty weight (lb)
- 2,100
- Fuel capacity (gal)
- 300
- Max takeoff weight (lb)
- 3,600
Performance
- Fuel burn (gph)
- 13.8
- Max crosswind (kt)
- 10
- Takeoff over 50ft
- 2,240
- Takeoff distance (ft)
- 1,360
V-speeds
- VR
- 63
- VS1
- 58.5
Weight & balance
- Useful load (lb)
- 1,290
- Basic empty weight (lb)
- 2,100
- Max takeoff weight (lb)
- 3,600
Common. Rarer than 8% of the aircraft models we track.
Most owners only have the POH. Here's the essential set for the Piper PA-11 Cub Special.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins
- Type Certificate (TCDS)
Free — save the PA-11 Cub Special to your watchlist and track it in one place.
More Piper PA-11 Cub Specialmanuals & documents
- Airworthiness Directives; FS 2001 Corp, FS 2002 Corporation, FS 2003 Corporation, Piper, and Piper Aircraft, Inc. AirplanesService Bulletins
- PA-11 Cub SpecialPilot's Operating Handbook
- Montana Department of Transportation Aeronautics Division Vol. 63, No. 8 August 2012Other Documents
- Procedure Manual No. 1Training Manual
- SERVICE BULLETIN No. 868Service Bulletins
- Supplemental Type Certificate for the Piper PA-11 Cub SpecialSupplemental Type Certificate
If you fly the Piper PA-11 Cub Special, you may also be researching these.
In this document
Takeoff Performance
The takeoff performance section outlines the required distances for takeoff under various weight and environmental conditions. For a standard day at sea level, the takeoff distance is approximately 1,200 feet with a maximum weight of 1,600 lbs.
Climb Performance
Climb performance details the rate of climb for the Piper PA-11. At maximum gross weight, the aircraft achieves a rate of climb of about 600 feet per minute at sea level.
Cruise Performance
Cruise performance data indicates that the Piper PA-11 can maintain a cruise speed of approximately 70 knots at 75% power settings, with fuel consumption around 5.5 gallons per hour.
Landing Performance
Landing performance metrics include landing distances required under various conditions. The landing distance is approximately 1,000 feet on a hard surface at maximum weight.
Weight and Balance
This section provides guidelines for weight and balance calculations, emphasizing the importance of maintaining the center of gravity within specified limits for safe operation.
Safety notes
- Ensure weight and balance calculations are performed before flight.
- Adhere to specified takeoff and landing distances to ensure safety.
Full document text
TABLE OF CONTENTS SECTION 5 PERFORMANCE Paragraph No. 5.1 General .. 5.3 5.5 Flight Planning Example. 5.7 Introduction to Performance and Flight Planning Performance Graphs List of Figures Page No. 5-1 5-1 5-3 5-7 5-7 REPORT: VB-890 5-i PIPER AIRCRAFT CORPORATION PA-32RT-300, LANCE II SECTION 5 PERFORMANCE SECTION 5° PERFORMANCE 5.1 GENERAL All of the required (FAA regulations) and complementary performance information applicable to the Lance II is provided by this section. Performance information associated with those optional systems and equipment which require handbook supplements is, provided by Section 9 (Supplements). 5.3 INTRODUCTION TO PERFORMANCE AND FLIGHT PLANNING The performance information presented in this section is based on measured Flight Test Data corrected to I.C.A.O. standard day conditions and analytically expanded for the various parameters of weight, altitude, temperature, etc. The performance charts are unfactored and do not make any allowance for varying degrees of pilot proficiency or mechanical deterioration of the aircraft. This performance, however, can be duplicated by following the stated procedures in a properly maintained airplane. Effects of conditions not considered on the charts must be evaluated by the pilot, such as the effect of soft or grass runway surface on takeoff and landing performance, or the effect of winds aloft on cruise and range performance. Endurance can be grossly affected by improper leaning procedures, and inflight fuel flow quantity checks are recommended. REMEMBER. To get chart performance, follow the chart procedures. The information provided by paragraph 5.5 (Flight Planning Example) outlines a detailed flight plan using performance charts in this section. Each chart includes its own example to show how it is used. ISSUED: JANUARY 18, 1978 REPORT: VB-890 REVISED: DECEMBER 15, 1978 5-1 SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPORATION PA-32RT-300, LANCE II THIS PAGE INTENTIONALLY LEFT BLANK REPORT: VB-890 5-2 ISSUED: JANUARY 18, 1978 PIPER AIRCRAFT CORPORATION PA-32RT-300, LANCE II SECTION 5 PERFORMANCE 5.5 FLIGHT PLANNING EXAMPLE (a) Aircraft Loading The first step in planning our flight is to calculate the airplane weight and center of gravity by utilizing the information provided by Section 6 (Weight and Balance) of this handbook. The basic empty weight for the airplane as delivered from the factory has been entered in Figure 6-5. If any alterations to the airplane have been made effecting weight and balance, reference to the aircraft logbook and Weight and Balance Record (Figure 6-7) should be made to determine the current basic empty weight of the airplane. Make use of the Weight and Balance Loading Form (Figure 6-11) and the C.G. Range and Weight graph (Figure 6-15) to determine the total weight of the airplane and the center of gravity position. After proper utilization of the information provided we have found the following weights for consideration in our flight planning example. The landing weight cannot be determined until the weight of the fuel to be used has been established [refer to item (g)(1)]. (1) Basic Empty Weight (2) Occupants (6 x 170 lbs) (3) Baggage and Cargo (4) Fuel (6 lb/gal x 50) (a)(5) minus (g)(1), (3480 lbs. minus 90 lbs.) 2100 lbs. 1020 lbs. 60 lbs. 300 lbs. 3480 lbs. 3390 lbs. (5) Takeoff Weight (6) Landing Weight Our takeoff weight is below the maximum of 3600 lbs. and our weight and balance calculations have determined our C.G. position within the approved limits. (b) Takeoff and Landing Now that we have determined our aircraft loading, we must consider all aspects of our takeoff and landing. All of the existing conditions at the departure and destination airport must be acquired, evaluated and maintained throughout the flight. Apply the departure airport conditions and takeoff weight to the appropriate Takeoff Performance and Takeoff Ground Roll graph (Figures 5-5, 5-7, 5-9, and 5-11) to determine the length of runway necessary for the takeoff and/or the barrier distance. The landing distance calculations are performed in the same manner using the existing conditions at the destination airport and, when established, the landing weight. ISSUED: JANUARY 18, 1978 REPORT: VB-890 5-3 SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPORATION PA-32RT-300, LANCE II The conditions and calculations for our example flight are listed below. The takeoff and landing distances required for our example flight have fallen well below the available runway lengths. Departure Airport Destination Airport (1) Pressure Altitude (2) Temperature (3) Wind Component I (4) Runway Length Available (5) Runway Required NOTE (c) Climb 1200 ft. 15.6°C 10 KTS 3000 ft. 2240 ft.* The remainder of the performance charts used in this flight plan example assume a no wind condition. The effect of winds aloft must be considered by the pilot when computing climb, cruise and descent performance. 400 ft. 23.9° C 0 KTS 4600 ft. 1740 ft.** The next step in our flight plan is to determine the necessary climb segment components. The desired cruise pressure altitude and corresponding cruise outside air temperature values are the first variables to be considered in determining the climb components from the Fuel, Distance, and Time to Climb graph (Figure 5-17). After the fuel, distance and time for the cruise pressure altitude and outside air temperature values have been established, apply the existing conditions at the departure field to graph (Figure 5-17). Now, subtract the values obtained from the graph for the field of departure conditions from those for the cruise pressure altitude. The remaining values are the true fuel, distance and time components for the climb segment of the flight plan corrected for field pressure altitude and temperature. The following values were determined from the above instructions in our flight planning example. (1) Cruise Pressure Altitude (2) Cruise OAT (3) Time to Climb (8 min. minus 1.5 min.)
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(4) Distance to Climb (14 nautical miles minus 3 nautical miles) (5) Fuel to Climb (3.2 gal. minus 0.4 gal.) 6000 ft. 5.6°C 6.5 min.*** 11 nautical miles *** 2.8 gal.*** *reference Figure 5-5 **reference Figure 5-33 ***reference Figure 5-17 REPORT: VB-890 5-4 ISSUED: JANUARY 18, 1978 REVISED: MARCH 27, 1978 PIPER AIRCRAFT CORPORATION PA-32RT-300, LANCE II SECTION 5 PERFORMANCE (d) Descent The descent data will be determined prior to the cruise data to provide the descent distance for establishing the total cruise distance. Utilizing the cruise pressure altitude and OAT we determine the basic fuel, distance and time for descent (Figure 5-29). These figures must be adjusted for the field pressure altitude and temperature at the destination airport. To find the necessary adjustment values, use the existing 224 pressure altitude and temperature conditions at the destination airport as variables to find the fuel, distance and time values from the graph (Figure 5-29). Now, subtract the values obtained from the field conditions from the values obtained from the cruise conditions to find the true distance and time values needed for the flight plan. Bifuel, The values obtained by proper utilization of the graphs for the descent segment of our example are shown below. (1) Time to Descend (12.5 min. minus 2.5 min.) 10 min.* (2) Distance to Descend (33 nautical miles minus 7 nautical miles) (3) Fuel to Descend (4 gal. minus 1 gal.) 26 nautical miles* 3 gal.* (e) Cruise Using the total distance to be traveled during the flight, subtract the previously calculated distance to climb and distance to descend to establish the total cruise distance. Refer to the appropriate Avço Lycoming Operator's Manual and the Power Setting Table (Figure 5-19) when selecting the cruise power setting. The established pressure altitude and temperature values and the selected cruise power should now be utilized to determine the true airspeed from the appropriate Speed Power graph (Figure 5-21 or 5-23).. Calculate the cruise fuel flow for the cruise power setting from the information provided by the Avco Lycoming Operator's Manual. The cruise time is found by dividing the cruise distance by the cruise speed and the cruise fuel is found by multiplying the cruise fuel flow by the cruise time. The cruise calculations established for the cruise segment of our flight planning example are as follows: (1) Total Distance 130 nautical miles (2) Cruise Distance (3) Cruise Power (4) Cruise Speed (e)(1) minus (c)(4) minus (d)(2), (130 nautical miles minus 11 nautical miles minus 26 nautical milės) (5) Cruise Fuel 93 nautical miles 65% rated power 142 KTS TAS** 13.8 GPH (6) Cruise Time (e)(2) divided by (e)(4), (93 nautical miles divided by 142 KTS) (7) Cruise Fuel (e)(5) multiplied by (e)(6), (13.8 GHP multiplied by .66 hrs.) *reference Figure 5-29 .66 hrs. (40 min.) 9.11 gal. **reference Figure 5-23 ISSUED: JANUARY 18, 1978 026-07 REPORT: VB-890 5-5 SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPORATION PA-32RT-300, LANCE II (f) Total Flight Time The total flight time is determined by adding the time to climb, the time to descend and the cruise time. Remember! The time values taken from the climb and descent graphs are in minutes and must be converted to hours before adding them to the cruise time. The following flight time is required for our flight planning example. (1) Total Flight Time (c)(3) plus (d)(1) plus (e)(6), (.11 hrs. plus .17 hrs. plus .66 hrs.) (6.5 min. plus 10 min. plus 40 min.) (g) Total Fuel Required 56.5 min. Determine the total fuel required by adding the fuel to climb, the fuel to descend and the cruise fuel. When the total fuel (in gallons) is determined, multiply this value by 6 lb/gal to To determine the total fuel weight used for the flight. The total fuel calculations for our example flight plan are shown below. (1) Total Fuel Required (c)(5) plus (d)(3) plus (e)(7), (2.8 gal. plus 3.0 gal. plus 9.11 gal.) 14.91 gal. multiplied by 6 lb/gal.) 14.91 gal. 90 lbs. REPORT: VB-890 5-6 ISSUED: JANUARY 18, 1978 PER AIRCRAFT CORPORATION A-32RT-300, LANCE II 5.7 PERFORMANCE GRAPHS SECTION 5 PERFORMANCE LIST OF FIGURES Page No. 5-9 5-10 5-11 5-12 5-13 5-14 5-15 5-16 5-17 5-19 5-21 5-22 5-23 5-24 5-25 5-26 5-27 5-28 5-29 Figure No. 5-1 Airspeed System Calibration 5-3 Stall Speed vs Angle of Bank 5-5 5-7 Flaps Second Notch Takeoff Performance Flaps Second Notch Takeoff Ground Roll 5-9 Flaps Up Takeoff Performance 5-11 Flaps Up Takeoff Ground Roll 5-13 Gear Up Rate of Climb. . . 5-15 Gear Down Rate of Climb 5-17 Fuel, Distance and Time toClimb 5-19 Power Setting Table 5-21 Speed Power - Performance Cruise 5-23 5-25 5-27 Speed Power - Economy Cruise Range Endurance 5-29 Fuel, Distance and Time to Descend 5-31 Glide Range 5-33 Landing Performance 5-35 Landing Ground Roll 5-37 Landing Performance (Heavy Duty Group) 5-39 Landing Ground Roll (Heavy Duty Group) 5-30 ISSUED: JANUARY 18, 1978 REPORT: VB-890 5-7 SECTION 5 PERFORMANCE PIPER AIRCRAFT CORPORATION PA-32RT-300, LANCE II REPORT: VB-890 5-8 THIS PAGE INTENTIONALLY LEFT BLANK ISSUED: JANUARY 18, 1978 PIPER AIRCRAFT CORPORATION PA-32RT-300, LANCE II 190 180 170 160 150 140 130 120 110 100 90 .80 70 KCAS 60 PA-32RT-300 AIRSPEED SYSTEM CALIBRATION: GROSS WEIGHT, 3600 LBS. WING FLAPS FULL DOWN WING FLAPS UP 50 50 60 70 80 ISSUED: JANUARY 18, 1978 90 100 110 120 130 140 150 160 170 180 190 200 KIAS ZERO INSTRUMENT ERROR AIRSPEED SYSTEM CALIBRATIONS Figure 5-1 REPORT: VB-890 5-9 SECTION 5 PERFORMANCE 1 SECTION 5 PERFORMANCE Example: Flaps: Up STALL SPEED KIAS STALL SPEED KIAS 80 10 60 50 80 70 PIPER AIRCRAFT CORPORATION PA-32RT-300, LANCE II PA-32RT-300 STALL SPEED VS. ANGLE OF BANK GROSS WEIGHT, 3600 LBS. T 50 0 10 20 Angle of bank: 30° Stall speed: 58.5 KIAS REPORT: VB-890 5-10 FLAPS UP FLAPS FULL DOWN 30 40 50 60 ANGLE OF BANK - DEGREES STALL SPEED VS. ANGLE OF BANK Figure 5-3 ISSUED: JANUARY 18, 1978 REVISED: MARCH 27, 1978 ISSUED: JANUARY 18, 1978 FLAPS SECOND NOTCH TAKEOFF PERFORMANCE Figure 5-5 REPORT: VB-890 5-11 PA-32RT-300 FLAPS SECOND NOTCH TAKEOFF PERFORMANCE TTTTTTTTTT 2700 RPM & FULL THROTTLE BEFORE BRAKE RELEASE PAVED LEVEL DRY RUNWAY: CAUTION: T.O. DISTANCE IS INCREASED BY APPROXIMATELY 25% AT C.G.'S FWD OF 85 IN. TTTTTI T.O. SPEED-KIAS WT. LBS. LIFTOFF BARRIER 3600 63 65 3200 63 2800 62 63 2400 62 62 PRESSURE ALT.-FT. XX 7000 6000 2000 SEA LEVEL -30-20-10 0 10 20 OUTSIDE AIR TEMP.-°C Example: Outside air temp.: +16°C Airport pressure altitude: 1200 ft. Gross weight: 3480 lbs. Headwind: 10 kts. Takeoff distance: 2240 ft. REF. LINE REF. LINE: TAILWIND 5000 HEADWIND 4000 3000 PA-32RT-300, LANCE II PIPER AIRCRAFT CORPORATION TAKEOFF DISTANCE OVER 50FT. BARRIER-FT. 2000 1000 2800 2400 0 5 10 15 WEIGHT-LBS. WIND-KTS. 30 40 3600 3200 -33-300 PERFORMANCE SECTION 5 5-12 REPORT: VB-890 EDT FLAPS SECOND NOTCH TAKEOFF GROUND ROLL Figure 5-7 ISSUED: JANUARY 18, 1978 PA-32RT-300 FLAPS SECOND NOTCH TAKEOFF GROUND ROLL 2700 RPM & FULL THROTTLE BEFORE BRAKE RELEASE- PAVED LEVEL DRY RUNWAY. CAUTION: T.O. DISTANCE IS INCREASED BY APPROXIMATELY 25% AT C.G.'S FWD OF 85 IN. WT. LBS. T.O. SPEED -KIAS 3600 63 3200 63 2800 62 2400 62 PRESSURE ALT.-FT. 7000 6000 4000 2000 SEA LEVEL REF. LINE: LINEE REF. TAILWIND 0 10 20 30 40 3600 3200 2800 2400 WEIGHT-LBS -30-20-10 Example: OUTSIDE AIR TEMP.-°C Outside air temp.: +16°C Airport pressure altitude: 1200 ft. Gross weight: 3480 lbs. Headwind: 10 kts. Takeoff ground roll: 1360 ft. 3000 HEADWIND 2000 PERFORMANCE SECTION 5 TAKEOFF GROUND ROLL DIST.-FT. 1000 5 10 15 WIND-KTS. PIPER AIRCRAFT CORPORATION PA-32RT-300, LANCE II REVISED: MARCH 27, 1978 ISSUED: JANUARY 18, 1978 REPORT: VB-890 5-13 FLAPS UP TAKEOFF PERFORMANCE Figure 5-9 PA-32RT-300 TTTTTTTTT FLAPS UP TAKEOFF PERFORMANCE HUITI 2700 RPM & FULL THROTTLE BEFORE BRAKE RELEASE PAVED, LEVEL, DRY RUNWAY TTTTTTTTTTt CAUTION: T.O. DISTANCE IS INCREASED BY APPROXIMATELY 25% AT C.G.'S FWD OF 85 IN. T.O. SPEED-KIAS WT. LBS. LIFTOFF BARRIER 3600 70 74 3200 69 2800 67 2400 66 68 PRESSURE ALT.-FT. 7000 6000 5000 4000 3000 2000 1000; SEA LEVEL REF. LINE: -30-20-10 OUTSIDE AIR TEMP.-°C 10 20 30 40 3600 3200 WEIGHT-LBS. Example: Outside air temp.: +16° C Airport pressure altitude: 1200 ft. Gross weight: 2800 lbs. Headwind: 10 kts. Takeoff distance: 1610 ft. V-338 2800 2400 0 REF. LINE: TAILWIND 6000 SHEADWIND 5000 4000 5 10 15 WIND-KTS. 3000 2000 1000 TAKEOFF DISTANCE OVER 50FT. BARRIER-FT. PA-32RT-300, LANCE II PIPER AIRCRAFT CORPORATION PERFORMANCE SECTION 5 REPORT: VB-890 5-14 85608 REVISED: SEPTEMBER 7, 1978 ISSUED: JANUARY 18, 1978 FLAPS UP TAKEOFF GROUND ROLL Figure 5-11 PA-32RT-300 FLAPS UP TAKEOFF GROUND ROLL TITITTTTTTTTTTTT 2700 RPM & FULL THROTTLE BEFORE BRAKE RELEASE] PAVED LEVEL DRY RUNWAY- CAUTION: T.O. DISTANCE IS INCREASED BY APPROXIMATELY 25% AT C.G.'S FWD OF 85 IN. PRESSURE ALT FT. 7000 6000 5000 4000 30007 2000 1000 SEA LEVEL REF. LINE WT. LBS. T.O. SPEED-KIAS LIFTOFF 3600 70 3200 69 2800 67 2400 66 976 REF. LINE- TAILWIND 4000 3000 HEADWIND 2000 1000 8 -30-20-10 OUTSIDE AIR TEMP.-°C 0 10 20 30 40 3600 3200 2800 2400 WEIGHT-LBS. 05 10 15 WIND-KTS. Example: Outside air temp.: +16°C Airport pressure altitude: 1200 ft. Gross weight: 2800 lbs. Headwind: 10 kts. Takeoff ground roll: 1000 ft. TAKEOFF GROUND ROLL DIST.-FT. PERFORMANCE SECTION 5 PIPER AIRCRAFT CORPORATION PA-32RT-300, LANCE II