1. DESCRIPTION.
This publication is issued as temporary instructions in lieu of the final publication which will be more complete.
The P-40N airplane is a single seat, low wing monoplane designed for medium altitude pursuit and interception of hostile aircraft. It is powered with one 12 cylinder V-1710-81 (F-20R) Allison engine for airplanes AF42-104429 through AF42-106405, and one 12 cylinder V-1710-99 (F-26R) Allison engine for airplanes AF42-106504 and subsequent. Its armament consists of six .50 caliber machine guns. All guns fire outside the propeller disc.
2. DIMENSIONS.
Figure 8 gives the principal overall dimensions with airplane in normal position at rest.
3. LEADING PARTICULARS.
The principal dimensions and data pertaining to the airplane are given in the following table.
PRINCIPAL DIMENSIONS.
(Aircraft in Level Flight Position unless otherwise stated.)
| GENERAL |
| Span | 37' 3.5" |
| Length (Overall) | 33' 3.72" |
| Height | 12' 7" |
| Height (Tail Wheel on Ground, Propeller
Blade Vertical at Top) | 13' 3.51" |
| WINGS |
Airfoil Section (Curve Identification)-
N.A.C.A.' 2215 at Root
N.A.C.A. 2209 at 19711 from fuselage |
| Chord at Root | 9' |
| Chord at Wing Tip | 46.62" |
| Incidence | +1° |
| Dihedral (Measured at leading edge at wing) | 6° |
| Sweep Back | 1°18' |
| STABILIZER |
| Span | 12' 9.62" |
| Maximum Chord | 42.75" |
| Incidence | +2° |
| FUSELAGE |
| Width (Maximum) | 38.32" |
| Height (Maximum) | 57.81" |
| Length (Without Engine Mount) | 21' 9.5"; |
| Length (With Engine Mount) | 27' 2"; |
AREAS
| WINGS (Less Ailerons) | 217.50 sq.ft. |
| WINGS (Total) | 236 sq. ft. |
| AILERONS (Total) | 18.41 sq. ft. |
| FLAPS (Total) | 34.8 sq. ft |
| STABILIZERS (Including Elevators) | 30.86 sq. ft. |
| ELEVATORS (Including Tabs) | 17.44 sq. ft. |
| ELEVATOR TRIM TABS (Total) | 1.68 sq. ft. |
| FIN | 7.0 sq. ft. |
| RUDDER (Including Tab) | 13.74 sq. ft. |
| RUDDER TRIM TAB | .55 sq. ft. |
|
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SETTINGS AND RANGES OF MOVEMENT OF CONTROL SURFACES
| STABILIZER | 2° Up from Thrust Line |
FIN, OFFSET (Degrees from
Fuselage Center Line) | 0° |
| AILERONS |
UP TRAVEL
(In Degrees from Neutral) | 18¾° |
DOWN TRAVEL
(In Degrees from Neutral) | 10½° |
| ELEVATORS |
UP TRAVEL (In Degrees from
Streamline with Stabilizer) | 30° ±2 |
DOWN TRAVEL (In Degrees,
from Streamline with Stabilizer) | 20° ±2 |
| RUDDER |
| RIGHT TRAVEL | 30° |
| LEFT TRAVEL | 30° |
| TRIM TABS |
| ELEVATOR |
UP TRAVEL (In Degrees
from Elevator Trailing Edge) | 3° |
DOWN TRAVEL (In Degrees
from Elevator Trailing Edge) | 26° |
| RUDDER |
RIGHT TRAVEL (In Degrees
from Rudder Trailing Edge | 30° |
LEFT TRAVEL (In Degrees
from Rudder Trailing Edge | 30° |
| AILERON |
LEFT AND RIGHT
Fixed and bent to suit, onthe ground |
| FLAPS |
| UP | 0° |
| DOWN | 45° |
| ALIGHTING GEAR |
Wheel Type Alighting Gear:Tread (Width from Center of Tread to Center of Tread
| 8'2.3" |
| SHOCK STRUTS (MAIN): |
| Type | Single strut, Pneumatic oleo |
| FLUID REQUIRED: |
Trade Name Identification
(Commercial) | Lockheed No. 5 |
| Army Air Forces Specification No. | 3856-C. |
| WHEELS (MAIN): |
| Tires | 30" smooth contour |
| Tire Pressure (Lbs. Sq. In.) | 40 Lb. |
| BRAKES: |
| Type | Hayes, hydraulic, single shoe |
| Tail Wheel: |
| SHOCK STRUTS: |
| Type | Single strut, Pneumatic oleo |
| FLUID REQUIRED: |
| Trade Name Identification (Com.) | Lockheed No. 5 |
| Army Air Forces Specification No | 3856-C |
| Tail Wheel: |
| WHEEL: |
| Tire | 12.5" diam., smooth contour |
| Tire Pressure (Lbs. Sq. In.) | 60 Lb. |
|
