GB1450965A - Rotor blades for rotorcraft - Google Patents
Rotor blades for rotorcraftInfo
- Publication number
- GB1450965A GB1450965A GB6001373A GB6001373A GB1450965A GB 1450965 A GB1450965 A GB 1450965A GB 6001373 A GB6001373 A GB 6001373A GB 6001373 A GB6001373 A GB 6001373A GB 1450965 A GB1450965 A GB 1450965A
- Authority
- GB
- United Kingdom
- Prior art keywords
- chord
- line
- aerofoil
- aerofoils
- naca
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/467—Aerodynamic features
Abstract
1450965 Aerofoils BOEING CO 28 Dec 1973 60013/73 Heading B7W An aerofoil, particularly for a helicopter rotor blade, has a profile developed from a NACA 6 series to provide a point of minimum pressure, at or about the design lift coefficient located less than 30% of the chord length behind the leading edge. As shown in the Figure the chord line c and the mean chord line m pass through the leading and trailing edges, the line m being determined by the equi-distant depths d along the chord. The maximum thickness t is expressed as a percentage of the chord and the aerofoil is defined by cartesian coordinates wherein the x axis is coincident with the chord line and the leading edge is the origin, and upper and lower offsets y. When tabulating the profile x and y are divided by the chord length to give x/c and y/c and the description includes tables setting out such co-ordinates for preferred aerofoil profiles. These were obtained by extrapolating from NACA sections having their point of minimum pressure located respectively at 30% and 40% chord to produce aerofoils denoted VR-7 and VR-8 having a t<SP>max</SP> at 12% and 8% chord.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB6001373A GB1450965A (en) | 1973-12-28 | 1973-12-28 | Rotor blades for rotorcraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB6001373A GB1450965A (en) | 1973-12-28 | 1973-12-28 | Rotor blades for rotorcraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1450965A true GB1450965A (en) | 1976-09-29 |
Family
ID=10484838
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB6001373A Expired GB1450965A (en) | 1973-12-28 | 1973-12-28 | Rotor blades for rotorcraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB1450965A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0037633A1 (en) * | 1980-03-28 | 1981-10-14 | WESTLAND plc | Helicopter rotor blade |
| GB2138374A (en) * | 1983-04-18 | 1984-10-24 | United Technologies Corp | Airfoil section for a rotor blade of a rotorcraft |
-
1973
- 1973-12-28 GB GB6001373A patent/GB1450965A/en not_active Expired
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0037633A1 (en) * | 1980-03-28 | 1981-10-14 | WESTLAND plc | Helicopter rotor blade |
| GB2138374A (en) * | 1983-04-18 | 1984-10-24 | United Technologies Corp | Airfoil section for a rotor blade of a rotorcraft |
| US4569633A (en) * | 1983-04-18 | 1986-02-11 | United Technologies Corporation | Airfoil section for a rotor blade of a rotorcraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4459083A (en) | Shapes for rotating airfoils | |
| US4412664A (en) | Family of airfoil shapes for rotating blades | |
| ES413589A1 (en) | Aircraft transporter | |
| US4142837A (en) | Helicopter blade | |
| GB1391939A (en) | Helicopter rotor blades | |
| JPH0627499U (en) | Air propeller | |
| GB1331025A (en) | Helicopter rotor blades | |
| Fletcher | Experimental investigation of lift, drag, and pitching moment of five annular airfoils | |
| GB1024963A (en) | Improvements in airfoil | |
| GB1485683A (en) | Helicopter rotor blade | |
| Lindsey et al. | Aerodynamics characteristics of 24 NACA 16-series airfoils at Mach numbers between 0.3 and 0.8 | |
| GB1343987A (en) | Airfoil for aircraft | |
| GB1144078A (en) | Compressor or like variable-camber aerofoil vanes | |
| GB1521530A (en) | Helicopter rotor blade having a selectively shaped and positioned ramp tab bonded thereto to eliminate blade pitching moment dynamic unbalance | |
| GB1391940A (en) | Helicopter rotor blades | |
| GB1450965A (en) | Rotor blades for rotorcraft | |
| CN103939283B (en) | Blade special for vertical axis wind turbine | |
| Graham et al. | Tests in the Ames 40-by 80-foot Wind Tunnel of an Airplane Configuration with an Aspect Ratio 2 Triangular Wing and an All-movable Horizontal Tail: Longitudinal Characteristics | |
| GB2400089A (en) | Aerofoil section | |
| GB605765A (en) | Improvements in or relating to aerofoil sections for low reynolds numbers | |
| CN109533314A (en) | A kind of light-duty unmanned helicopter Rotor Aerodynamics Shape | |
| GB615318A (en) | Improvements in or relating to low drag airfoils | |
| FR2261177A1 (en) | Aerodynamic rotor blade for helicopter - has an airfoil profile with component which has thickness distribution based on NACA series | |
| Riebe | A correlation of two-dimensional data on lift coefficient available with blowing-, suction-, slotted-, and plain-flap high-lift devices | |
| US1792015A (en) | Aerofoil |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PS | Patent sealed | ||
| PCNP | Patent ceased through non-payment of renewal fee |
Effective date: 19921228 |