AeroVantage 1x2 - Specifications

It is based on Prouty's Hover calculations

Item Nbr:

1681

January 2, 2009

Name:

AeroVantage 1x2 - (empty for BOM)

Text in black is input.

Text in blue is calculated.

PropRotor

Front

Rear

Blade:

Type of airfoil

VR-7

VR-7

deg.

Angle of attack for zero lift

-1.4

-1.4

Number of blades: [b]

3

3

Radius: [R]

5.5

4.375

ft.

Chord: [c]

0.5

0.5

ft.

Blade Area: [Ab]=[b*c*R]

8.25

6.56

sq-ft

Aspect Ratio: [R / c]

11

8.75

:1

Blade cutout ratio: [xo] (The blade root radius divided by the tip radius.)

0.1

0.1

Taper (not used at present) [cct]

Twist Type; 1 - none; 2 - linear; 3 - ideal.

2 or 3?

2 or 3?

Pitch that the blade would have if extended into center of rotation. [Theta_o]

26.5

28.8

deg.

Angle of twist (washout). Tip pitch - root pitch. i.e. negative value. [Theta1]

-24

-24

deg.

Pitch at the blade tip: [Theta_t] (for ideal only)

2.5

4.8

deg.

Hub:

Rotor Configuration: Single=1, Coaxial=2 ??

Hub to Neutral Point distance in hover. [??]

 8.611

 9.188

ft.

Coning Angle [a0]

4?

4?

deg

Disk:

Disk area (1 rotor); [A1]

 95.0

 60.0

sq-ft

Total disk area: [AT]

155.0

sq-ft

Effective disk area: [A]

sq-ft

Disk loading: [DL] (calculated using gross weight)

6.966

 11.009

lb/ft2

Blade Loading: [BL]

8.242

 100.88

lb/ft2

Rotor solidity ratio: [Sigma]

0.0868

 0.1091

%

Motor and Power Train:

Engine/Motor Nbr: (datebase identifier)

Make:

Model:

Ratio

Loss

RPM Hub: (Engine operation rpm divided by Ratio.)

 1000

 1250

rpm

Weight:

Empty Weight: [EW]

800

lb.

Load

525

lb.

Gross Weight: [GW = EW + Load]

1325

lb.

PropRotor

Front

Rear

Flight - Hovering:

Momentum Method

Disk Loading: [DL]

6.966

11.009

lb/ft2

Velocity: [V1hov] (Average of velocities through the disk.)

 38.27

 48.11

ft/sec

Power; [P] (see *) (Figure of Merit set to 0.65)

61.2 

79.6 

hp.

Power Loading: [PL] (for hover ONLY) (see *)

 10.8

8.3

lb/hp

Nondimensional Coefficients;

0.0088306

0.0141159

Thrust: [CT]

1.418E-06

2.964E-06

Power: [CP]

0.1017209

0.1293433

CT / Sigma

Combined Momentum and Blade Element Theory w/ Empirical Corrections

Coefficients of:-

Thrust: [CTntl] (w/o tip loss)

0.0099868

0.0146779

Tip loss factor: [B]

0.9624797

 0.9490983

Thrust: [CT] (with tip loss)

0.0093757

 0.0133061

Profile; [CQo]

0.0001091

 0.0001487

Induced: [CQi]

0.0005958

 0.0010462

Torque: [CQ]

0.0007451

 0.0012869

Power: [CP]

ROI CQi / Thrust CQi

Disk loading: [DL] (calculated using thrust)

7.3960

10.378

lb/ft2

Thrust Solidity: [CT/Sigma]

0.1080007

 0.1219231

[(DL)(CT/Sigma)]

0.7987769

 1.265262

Measured power / Calculated power

 1.055

 1.055

CQ / Sigma

 0.0085835

 0.0085835

Thrust: [T] (see *)

 703

 624

lb

Horsepower: [hp] (see *)

 58.9

 62.8

hp

Total Horsepower:

121.7

hp