Master Airscrew Scimitar 11×6

11×6×2 · air · measured geometry

Chord and twist are the UIUC digitization. Camber, thickness and the two-blade count are PropShaper lofting defaults, not measurements, and this prop is not in the BEMT validation gate. The hub starts as a conventional M5 and is yours to change.

Not a validation case. Loading this blade does not mean the solver has been checked against it. Use the measured table and the model as two sources.

Open this prop in the studio →

What the wind tunnel says

These figures are computed from the UIUC file, not from PropShaper's solver. Static thrust is T = C_T ρ n² D⁴ and power is P = C_P ρ n³ D⁵, with ρ = 1.225 kg/m³ (ISA sea level) and n in revolutions per second. Figure of merit is C_T^3/2 / (√2 C_P), the hovering-rotor definition. On this Volume 1 set it runs about 0.30–0.64. A helicopter near 0.75 is the wrong comparison.

Forward flight, one run

The run whose rpm is nearest 5,998 is shown in full. mas_11x6_kt0702_5998.txt. Other runs are linked under it. Advance ratio J = V / (n D).

UIUC measurement at 5,998 rpm. Solid line is thrust coefficient CT. Dashed line is propulsive efficiency. This is not a PropShaper prediction.

J	CT	CP	η
0.087	0.0884	0.0400	19%
0.108	0.0873	0.0403	23%
0.132	0.0857	0.0407	28%
0.153	0.0836	0.0409	31%
0.174	0.0815	0.0413	34%
0.199	0.0789	0.0414	38%
0.219	0.0771	0.0415	41%
0.241	0.0740	0.0414	43%
0.262	0.0698	0.0409	45%
0.285	0.0658	0.0403	47%
0.306	0.0623	0.0397	48%
0.323	0.0591	0.0390	49%
0.347	0.0555	0.0383	50%
0.369	0.0521	0.0375	51%
0.389	0.0497	0.0368	53%
0.410	0.0471	0.0360	54%
0.433	0.0438	0.0348	55%

Other measured rpm

rpm	best η	at J	file
3010	45%	0.436	mas_11x6_kt0697_3010.txt
3997	43%	0.554	mas_11x6_kt0699_3997.txt
4004	49%	0.490	mas_11x6_kt0698_4004.txt
5008	52%	0.466	mas_11x6_kt0700_5008.txt
5008	52%	0.465	mas_11x6_kt0701_5008.txt
5998	55%	0.433	mas_11x6_kt0702_5998.txt

Geometry the studio loads

r/R, chord/radius and twist from mas_11x6_geom.txt. The geometry file does not record blade count. This commercial prop is loaded as two blades, which matches the three props the solver is checked against. Camber and thickness are PropShaper lofting defaults (slow-flyer families cambered, others near 2% camber), not the manufacturer's section. The hub starts as a conventional M5. Change it to your motor.

r/R	c/R	twist deg
0.15	0.155	31.62
0.20	0.153	30.79
0.25	0.152	29.07
0.30	0.151	27.19
0.35	0.151	25.39
0.40	0.150	23.63
0.45	0.150	21.99
0.50	0.149	20.43
0.55	0.146	18.90
0.60	0.143	17.45
0.65	0.138	16.10
0.70	0.132	14.70
0.75	0.125	13.43
0.80	0.116	12.28
0.85	0.106	10.97
0.90	0.095	9.45
0.95	0.075	7.79
1.00	0.055	6.11

Sources

UIUC Volume 1 mas_11x6_geom.txt

UIUC Propeller Database, Volume 1, version 3, compiled by Gavin Ananda, 3 February 2015. Files were fetched 2026-10-09.
Brandt, J. B., and Selig, M. S., “Propeller Performance Data at Low Reynolds Numbers,” 49th AIAA Aerospace Sciences Meeting, AIAA Paper 2011-1255, January 2011. PDF.
Brandt, J. B., “Small-Scale Propeller Performance at Low Speeds,” M.S. Thesis, University of Illinois at Urbana-Champaign, 2005. The Volume 1 page says these online files include a wind-tunnel correction that post-dates the thesis, and that the online files should be used rather than the thesis tables. Thesis · correction note.

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