--- title: 'Angle of attack vs pitch angle' description: 'Understand angle of attack vs pitch angle with a clear diagram and worked examples. Learn why a nose-down aircraft can still have a positive angle of attack.' lastModified: 2026-10-31 --- **Pitch angle tells you where the aircraft’s nose points relative to the horizon. Angle of attack tells you how the wing meets the oncoming air.** The missing piece is the flight path: the direction the aircraft is moving through the air. A nose-up aircraft may be climbing, flying level, or descending. You need its flight path to tell which. [4](https://www.icao.int/sites/default/files/safety/LOCI/AUPRTA/full.html). ## Pitch angle uses the horizon **Pitch angle**, also called **pitch attitude**, is the angle between the aircraft’s longitudinal axis and the horizon. Imagine a reference line running fore and aft through the aircraft. Nose-up pitch is positive; nose-down pitch is negative. The attitude indicator shows this relationship against an artificial horizon. It gives you pitch attitude; it does not measure wing angle of attack. [3](https://www.faa.gov/sites/faa.gov/files/10_phak_ch8.pdf#page=18). ## Angle of attack uses the relative airflow The **chord line** is a straight line joining the leading and trailing edges of a wing section. **Wing angle of attack (AOA)** is the angle between that line and the oncoming airflow. [1](https://www.faa.gov/sites/faa.gov/files/07_phak_ch5_0.pdf#page=2), [2](https://www.faa.gov/sites/faa.gov/files/21_phak_glossary.pdf#page=6). **Relative airflow**, also called **relative wind**, is the air’s motion as seen from the aircraft. In a simple side view, it flows parallel to the aircraft’s path through the air, in the opposite direction. If you draw a climbing flight path, draw the airflow along the same slope with its arrow pointing back towards the aircraft. [2](https://www.faa.gov/sites/faa.gov/files/21_phak_glossary.pdf#page=25). | Quantity | Lines you compare | What it describes | | -------------------- | -------------------------------------------------- | ----------------------------------- | | Pitch angle | Aircraft’s longitudinal axis and horizon | Where the nose points | | Wing angle of attack | Wing chord line and relative airflow | How the wing meets the air | | Flight-path angle | Direction of travel through the air and horizontal | Whether that path slopes up or down | The **flight-path angle** tells you how steeply the aircraft’s path slopes above or below horizontal. It is positive in a climb and negative in a descent. [4](https://www.icao.int/sites/default/files/safety/LOCI/AUPRTA/full.html). ## How pitch, angle of attack, and flight path fit together The diagram below shows wings-level flight in still air, with the wing chord aligned with the aircraft’s longitudinal axis. That alignment is called **zero wing incidence**. Measure pitch and flight-path angle from the same horizontal line. The gap between them is the angle of attack: **Angle of attack = pitch angle − flight-path angle** You will also see this written as **α = θ − γ**. Here, α (alpha) is angle of attack, θ (theta) is pitch, and γ (gamma) is flight-path angle. [4](https://www.icao.int/sites/default/files/safety/LOCI/AUPRTA/full.html). ![Side-view geometry: pitch theta lies between the horizontal and the aligned body and chord line; flight-path angle gamma lies below it; angle of attack alpha is the gap between those two inclined lines. Relative airflow points opposite travel.](/blume-assets/content/content/knowledge/principles-of-flight/angle-of-attack-vs-pitch.png) _Angles enlarged for clarity. The relative-airflow arrow runs parallel to the flight path and points in the opposite direction._ Still air lets us use the same path relative to the ground and the air. In wind, use the path **through the air** for this relationship; the path over the ground may differ. If the wing chord is tilted relative to the aircraft’s longitudinal axis, you need to include that mounting angle. It is called the **angle of incidence**, written here as _i_, and is positive when the chord is tilted nose-up relative to the body axis. [2](https://www.faa.gov/sites/faa.gov/files/21_phak_glossary.pdf#page=4). The chord then sits at **θ + i** above horizontal, so the same geometry gives **wing α = θ + i − γ**. Check the reference line in a question or diagram. Some use the body axis to define aircraft AOA; others use the wing chord. With non-zero incidence, those angles differ. [4](https://www.icao.int/sites/default/files/safety/LOCI/AUPRTA/full.html). ## The same angle of attack in a climb and a descent Try three hypothetical cases using the same still-air model, with zero wing incidence: | Example | Pitch angle θ | Flight-path angle γ | Angle of attack α | | ---------- | ------------: | ------------------: | -------------------: | | Climbing | +12° | +8° | 12° − 8° = **4°** | | Level | +4° | 0° | 4° − 0° = **4°** | | Descending | −2° | −6° | −2° − (−6°) = **4°** | In the climb, the nose points 12° above horizontal, but the aircraft travels along a path only 8° above horizontal. The gap is 4°. In the descent, the nose points below the horizon. The path slopes down more steeply than the chord, leaving the same positive 4° angle of attack. Sketch that descending case before calculating it. All three cases have the same AOA. Their airspeeds, lift forces, and power settings need not be the same. ## Why pitch attitude alone cannot identify a stall A wing stalls when it exceeds its **critical angle of attack**: airflow separation causes lift to decrease, though it does not disappear completely. The wing’s angle to the airflow determines this, so a stall can occur with the nose above or below the horizon. [1](https://www.faa.gov/sites/faa.gov/files/07_phak_ch5_0.pdf#page=25). The critical angle depends on the wing and conditions, including configuration, contamination, and Mach number. The 4° used in our examples was chosen to illustrate the geometry; it is not a stall limit. [4](https://www.icao.int/sites/default/files/safety/LOCI/AUPRTA/full.html). To calculate lift, you need more than AOA. Airspeed, air density, wing area, and lift coefficient all matter. The coefficient includes the effects of the wing’s shape and its angle to the airflow. [5](https://www1.grc.nasa.gov/beginners-guide-to-aeronautics/lift-equation/). ## Check your understanding Use the same zero-incidence model. An aircraft has a pitch angle of **−3°** and a flight-path angle of **−7°**. 1. Is it climbing or descending through the air? 2. Is its angle of attack positive or negative? 3. Can you tell whether the wing is stalled from those angles alone? **Answer:** The aircraft is descending, and its AOA is positive: **−3° − (−7°) = +4°**. The path slopes down more steeply than the chord. To decide whether the wing is stalled, you would also need the critical AOA for that wing and those conditions. When a question gives you an aircraft attitude, sketch its flight path too. Then label the angle between the lines the question actually names. ## References 1. [FAA, _Pilot’s Handbook of Aeronautical Knowledge_, FAA-H-8083-25C, Chapter 5](https://www.faa.gov/sites/faa.gov/files/07_phak_ch5_0.pdf): AOA definition, p. 5-2; stalls, p. 5-25. 2. [FAA handbook glossary](https://www.faa.gov/sites/faa.gov/files/21_phak_glossary.pdf): angle of incidence, p. G-4; chord line, p. G-6; relative wind, p. G-25. 3. [FAA handbook, Chapter 8](https://www.faa.gov/sites/faa.gov/files/10_phak_ch8.pdf): attitude indicator, p. 8-18. 4. [ICAO and aircraft manufacturers, _Airplane Upset Prevention and Recovery Training Aid_, Revision 3.0](https://www.icao.int/sites/default/files/safety/LOCI/AUPRTA/full.html): angle definitions and stalls, section 6.4.1; icing effects, section 6.6. 5. [NASA Glenn Research Center, “Lift Equation”](https://www1.grc.nasa.gov/beginners-guide-to-aeronautics/lift-equation/): factors affecting lift and the lift coefficient.