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Aircraft designs aim to balance two key objectives: maximizing lift surfaces to enable flight at lower speeds, and minimizing the cross-sectional area of the wing profile to reduce energy loss due to aerodynamic drag. Therefore, it is essential to compare and optimize both surfaces.
For wings, parameters such as span, thickness, and chord (width) can be adjusted to reduce the frontal area exposed to the airflow, thereby minimizing drag, while maximizing the wing surface, which is the primary source of lift. This approach allows for more efficient design, balancing lift and drag to achieve optimal flight performance.
ID:(2116, 0)
Aspect Ratio
Description
The aspect Ratio ($\gamma_w$) is defined as the ratio between the wing width ($w$) and the wing span ($L$), indicating the proportion or relationship between these two variables:
| $ \gamma_w =\displaystyle\frac{ w }{ L }$ |
Below are typical values of $w/L$ (the ratio between the wing chord and wingspan) according to the type of aircraft:
| Type of Aircraft | $w/L$ | Description |
| Commercial aircraft | 0.083-0.125 | Designed for maximum efficiency in cruise flight, minimizing induced drag during long-range flights. |
| Gliders | 0.033-0.066 | Optimized for gliding, with minimal drag and maximum lift for sustained flight without an engine. |
| Combat aircraft | 0.200-0.333 | Prioritize maneuverability and the ability to withstand high loads during fast maneuvers and supersonic flight. |
| Sports/acrobatic aircraft | 0.167-0.250 | Balanced between maneuverability and aerodynamic control, ideal for quick and precise maneuvers. |
| Light training aircraft | 0.100-0.143 | More stable wings that facilitate control at moderate speeds, essential for safe flight during training. |
This table highlights the differences in the $w/L$ ratio according to the purpose of each type of aircraft, reflecting variations in aerodynamic design and flight performance.
ID:(15978, 0)
Thickness ratio
Description
The aspect Ratio ($\gamma_w$) can be defined as the thickness to span ratio ($\gamma_d$), which establishes the relationship between the wing width ($w$) and the wing height ($d$) as follows:
| $ \gamma_r =\displaystyle\frac{ d }{ w }$ |
Below are typical values of $d/w$ (the ratio of wing thickness to chord) according to the type of aircraft:
| Type of Aircraft | $d/w$ | Description |
| Commercial Aircraft | 0.10-0.15 | Thin wings for maximum efficiency in cruise flight, optimizing lift and reducing aerodynamic drag. |
| Gliders | 0.08-0.12 | Extremely thin wings to minimize drag and allow for efficient gliding over long periods. |
| Combat Aircraft | 0.04-0.08 | Thicker wings to withstand high loads during extreme maneuvers and supersonic flight. |
| Sport/Acrobatic Aircraft | 0.10-0.14 | Relatively thin wings to provide good maneuverability with moderate aerodynamic efficiency. |
| Light Training Aircraft | 0.12-0.16 | Thicker wings for greater structural strength and easier handling at low speeds. |
This table illustrates how the $d/w$ ratio varies depending on the type of aircraft, reflecting specific design needs to maximize efficiency, maneuverability, or structural stability.
ID:(15977, 0)
Thickness to span ratio
Description
The thickness to span ratio ($\gamma_d$) is defined as the ratio between the wing height ($d$) and the wing span ($L$), expressed as follows:
| $ \gamma_d =\displaystyle\frac{ d }{ L }$ |
Below are typical values of $d/L$ (the ratio of wing thickness to wingspan) according to the type of aircraft:
| Type of Aircraft | $d/L$ | Description |
| Commercial Aircraft | 0.029-0.050 | Thin wings to improve aerodynamic efficiency during long-range cruise flights, minimizing drag. |
| Gliders | 0.020-0.033 | Extremely thin wings to reduce drag and maximize efficient gliding. |
| Combat Aircraft | 0.050-0.100 | Thicker wings to withstand high forces during high-speed maneuvers and maintain structural stability. |
| Sport/Acrobatic Aircraft | 0.040-0.083 | Relatively thick wings to improve maneuverability and support loads during acrobatic maneuvers. |
| Light Training Aircraft | 0.040-0.067 | Thicker wings to provide greater stability and resistance at low speeds, crucial for safe training. |
This overview illustrates how the $d/L$ ratio varies depending on the type of aircraft, reflecting different design priorities, such as aerodynamic efficiency, maneuverability, or structural stability.
ID:(15979, 0)
Thickness to span ratio
Description
The surface ratio ($\gamma$) is defined as the ratio between the total object profile ($S_p$) and the wing mass ($m_w$), represented as follows:
| $ \gamma =\displaystyle\frac{ S_p }{ S_w }$ |
Typical values for this factor across different aircraft types are detailed below:
| Type of Aircraft | $S_p/S_w$ | Description |
| Commercial aircraft | 0.01-0.02 | Designed for maximum efficiency in cruise flight, commercial aircraft maintain a relatively small frontal area compared to the wing area to reduce aerodynamic drag while providing enough lift to sustain efficient high-speed flight. |
| Gliders | 0.005-0.01 | Gliders are optimized for maximum aerodynamic efficiency, with a very small frontal area and large wing area to maximize lift and minimize drag, allowing them to glide long distances without a motor. |
| Combat aircraft | 0.02-0.03 | Combat aircraft prioritize maneuverability and agility, which results in a larger frontal area relative to the wing size. While this increases drag, it is justified by engine power and the need for quick maneuvers. |
| Sport/Acrobatic aircraft | 0.015-0.025 | These aircraft are designed for rapid maneuvers and high roll rates, requiring a balance between lift and drag to allow precise control and maneuverability, though with relatively lower aerodynamic efficiency compared to cruise aircraft. |
| Light or training aircraft | 0.01-0.02 | These aircraft are designed to be easy to fly and efficient at lower speeds. The balance between frontal and wing area provides good lift and maneuverability while keeping drag relatively low. |
This table illustrates how the $S_p/S_w$ ratio varies by aircraft type, reflecting differences in aerodynamic design to optimize lift, maneuverability, and flight efficiency.
ID:(15981, 0)
Aspect Ratio
Equation
The aspect Ratio ($\gamma_w$) is defined as the ratio between the wing width ($w$) and the wing span ($L$), indicating the proportion or relationship between these two variables:
 $ \gamma_w =\displaystyle\frac{ w }{ L }$ |
ID:(4551, 0)
Thickness ratio
Equation
The aspect Ratio ($\gamma_w$) can be defined as the thickness to span ratio ($\gamma_d$), which relates the wing width ($w$) to ($$)6338
| $ \gamma_r =\displaystyle\frac{ d }{ w }$ |
ID:(4555, 0)
Thickness to span ratio
Equation
The thickness to span ratio ($\gamma_d$) is defined as the ratio of the wing height ($d$) to the wing span ($L$), represented as follows:
| $ \gamma_d =\displaystyle\frac{ d }{ L }$ |
ID:(15976, 0)
Thickness to span ratio
Equation
The surface ratio ($\gamma$) is defined as the ratio between the total object profile ($S_p$) and the wing mass ($m_w$), expressed as follows:
| $ \gamma =\displaystyle\frac{ S_p }{ S_w }$ |
ID:(15980, 0)
Wing area
Equation
The surface that generates lift ($S_w$) can be estimated by multiplying the wing span ($L$) and the wing width ($w$), as follows:
| $ S_w = L w $ |
ID:(15982, 0)