Performance Calcs - windgen.org discussion

Senior Member

Status: Offline

Posts: 226

Date: 5 days ago

RE: Performance Calcs

Caleb i have to calibrate once: i have good simulations with naca2222 how do you mount the camber inside or outside. My script tells me outside but that does not fit with the theory of the wing on the circle ? __________________

Bob Mann

Senior Member

Status: Offline

Posts: 248

Date: 8 days ago

RE: Performance Calcs

That would be great I would love to look it over. I know mine makes more power than the stock C and a lower start-up speed right now. If you wish just send it to my email. bobtec@comcast.net Bob Mann __________________

brother paul

Senior Member

Status: Offline

Posts: 226

Date: 8 days ago

RE: Performance Calcs

i will send you a drawing in google sketchup so you can print the design Your c-rotor turbine is approx 10-15% efficient mine is 40-45% efficient So this means for the same square surfaceyour tipspeed will be approx 1, my tipspeed will be 3, i generate 3 times more energy for the same device on your roof. __________________

Bob Mann

Senior Member

Status: Offline

Posts: 248

Date: 9 days ago

Performance Calcs

Thank you for the return post. This is what I have learned on performance of these small turbines. As I am a hands on guy. the turbine must be free starting at low speeds below 10 MPH this is with a PMA installed. I know we have missed the boot on matching PMA to Load device till now. Using Steve,s Smart Controller I have learned a few things of matching Load to turbine/PMA. If you view my YouTube on the Controller you can get feel for what we do with matching loads. Bob Mann -- Edited by Bob Mann on Monday 13th of February 2012 03:45:43 PM __________________

brother paul

Senior Member

Status: Offline

Posts: 226

Date: 9 days ago

RE: Performance Calcs

yes, but its a drag machine... so the script does not work, it converts lift drag to Ctangential Cnormal, but in that case it does not work, i tried some angles of attack SO what i mean is, dont think this script is 'all saints guru' for predicting performance of your c-rotor __________________

Bob Mann

Senior Member

Status: Offline

Posts: 248

Date: 9 days ago

RE: Performance Calcs

Did you ever do the numbers for a stock C rotor blade? I am not all that sharp on your math hear. Bob Mann __________________

brother paul

Senior Member

Status: Offline

Posts: 226

Date: 9 days ago

Performance Calcs

selection high efficiency / low rotation speed comes with higher solidity, symmetrical profiles

also the naca series, since in a darrieus concept has at top and bottom an higher solidity, has alle- variations of windspeed to startup

Version:1.0 StartHTML:0000000157 EndHTML:0000008709 StartFragment:0000000492 EndFragment:0000008690

naam	maxCp	maxCptsr	ClCd	AoA	solid	profielnr
naca-0014	32.1	1.6	0	0	0.19	271
E476	31.9	1.6	0	0	0.19	394
S1048 14% (Danny Howell)	31.7	1.6	0	0.5	0.24	618
naca-0016	31.4	1.6	0	0.5	0.19	384
NACA 0017	31.2	1.6	0	1	0.14	2
US1000ROOT	30.9	1.6	0	0	0.19	1594
US1000ROOT	30.8	1.6	0	0.5	0.19	1594
GOE 775	30.6	1.6	0	0.5	0.14	907
E476	30.5	1.6	0	0.5	0.19	394
NACA 23024	30.4	1.6	0	-1	0.14	1698
NACA 0021	30.4	1.6	0	0.5	0.14	1713
NACA 66-018	30.4	1.6	0	0	0.19	1651
GOE 410	30.4	1.6	0	0.5	0.19	215
naca-0018	34.1	1.8	0	0.5	0.14	1240
NACA 0021	30.3	1.6	0	0	0.14	1713
EPPLER 428	30.2	1.6	0	0	0.19	404
S1016	30.1	1.6	0	0.5	0.19	1611
S1046 17% (Danny Howell)	33.7	1.8	0	0.5	0.14	693
E487	33.6	1.8	0	0.5	0.14	819
naca-0016	33.5	1.8	0	0.5	0.14	384
S8035 for RC aerobatic 14% thick	29.7	1.6	0	0	0.24	490
ULTIMATE	29.7	1.6	0	2	0.29	57
FX 76-120	29.7	1.6	0	0	0.24	1231
NASA/LANGLEY LS(1)-0013	29.6	1.6	0	0.5	0.24	1276
E169 (14.4%)	29.6	1.6	0	0	0.24	673
GOE 776	33.2	1.8	0	0	0.1	186

-- Edited by brother paul on Monday 13th of February 2012 12:10:17 PM

__________________

brother paul

Senior Member

Status: Offline

Posts: 226

Date: 9 days ago

Performance Calcs

list with high efficiency x high Rotation speed

normally high rotation means high reynolds, hence its possible since my simulation does not take in account the reynolds effect, they perform better. typical with low solidity

Version:1.0 StartHTML:0000000157 EndHTML:0000009346 StartFragment:0000000492 EndFragment:0000009327

EPPLER 479	35.5	3	0	0.1	1539
GOE 460	35.2	3	0.5	0.05	1340
RAF 69	30.8	3.4	0	0.05	1617
naca-2618	29	3.6	0	0.05	1151
naca-2518	28.9	3.6	0	0.05	1179
NACA 1415	27.3	3.8	0	0.05	1991
naca-2418	28.8	3.6	0	0.05	864
naca-2516	28.8	3.6	0	0.05	735
naca-2616	28.8	3.6	0	0.05	936
naca-2416	28.7	3.6	0	0.05	485
naca-2318	28.7	3.6	0	0.05	570
naca-2514	27.1	3.8	0	0.05	997
S1046 17% (Danny Howell)	32	3.2	0	0.05	693
naca-2316	28.4	3.6	0	0.05	479
naca-2414	26.9	3.8	0	0.05	88
P-51D ROOT (BL17.5)	26.9	3.8	0	0.05	1085
GOE 776	34	3	0	0.05	186
NACA 0024	34	3	0	0.05	1712
GOE 460	34	3	0	0.05	1340
NACA 0017	34	3	1	0.05	2
NACA 0024	33.8	3	0.5	0.05	1712
NACA 23024	33.8	3	0	0.05	1698
GOE 776	33.8	3	0.5	0.05	186
S8036 (16%)	28.1	3.6	0	0.05	1470
NACA 2415	28	3.6	0	0.05	1450
MH 95 15.86%	26.5	3.8	0	0.05	1746
NACA 2414	26.5	3.8	0	0.05	940

-- Edited by brother paul on Monday 13th of February 2012 12:03:05 PM

-- Edited by brother paul on Monday 13th of February 2012 12:09:09 PM

__________________

brother paul

Senior Member

Status: Offline

Posts: 226

Date: 10 days ago

RE: Performance Calcs

ok redone the complete bunch with ideal AoA

name	maxCptsr	maxCt	AoA	solid	profielnr
naca-0018	38.1	2.6	0.5	0.1	1240
S1046 17% (Danny Howell)	37.3	2.6	0	0.1	693
naca-0018	36.9	2.6	0	0.1	1240
naca-0016	36.6	2.6	0.5	0.1	384
S1046 17% (Danny Howell)	36.6	2.4	0.5	0.1	693
E475 (15.01%)	36.4	2.6	0.5	0.1	162
E474 (14.09%)	36.1	2.6	0.5	0.1	237
E476	36.1	2.6	0.5	0.1	394
S8035 for RC aerobatic 14% thick	35.7	2.4	0.5	0.14	490
S1014	35.7	2.6	0.5	0.1	1612
EPPLER 479	35.7	2.6	0.5	0.1	1539
E487	35.6	2.6	0.5	0.1	819
E169 (14.4%)	35.6	2.4	0.5	0.14	673
S1016	35.5	2.6	0.5	0.1	1611
S8035 for RC aerobatic 14% thick	35.5	2.6	0	0.1	490
EPPLER 479	35.5	3	0	0.1	1539
S8035 for RC aerobatic 14% thick	35.4	2.4	0	0.14	490
naca-0016	35.4	2.4	0	0.1	384
E169 (14.4%)	35.3	2.6	0	0.1	673
E475 (15.01%)	35.3	2.8	0	0.1	162
S1016	35.3	2.4	0	0.1	1611
GOE 410	35.2	2.6	0.5	0.1	215
GOE 460	35.2	3	0.5	0.05	1340
E476	35.1	2.6	0	0.1	394
E169 (14.4%)	35.1	2.6	0	0.14	673
GOE 775	35	2.2	0	0.1	907
Griffith 30% Suction Airfoil	35	2.6	0	0.05	1824
naca-0014	34.9	2.6	0.5	0.1	271
NACA 63(3)-018	34.9	2.6	0	0.1	1687
E169 (14.4%)	34.9	2.8	0.5	0.1	673

__________________

brother paul

Senior Member

Status: Offline

Posts: 226

Date: 10 days ago

Performance Calcs

OK grabbed complete worldofkrauss again, with the new script, i am more satisfied with the results

Version:1.0 StartHTML:0000000157 EndHTML:0000020342 Version:1.0 StartHTML:0000000157 EndHTML:0000012136 StartFragment:0000000492 EndFragment:0000012117

naam	maxCp	maxCptsr	solid	profielnr
S1046 17% (Danny Howell)	37.3	2.6	0.1	693
naca-0018	36.9	2.6	0.1	1240
S8035 for RC aerobatic 14% thick	35.5	2.6	0.1	490
EPPLER 479	35.5	3	0.1	1539
S8035 for RC aerobatic 14% thick	35.4	2.4	0.14	490
naca-0016	35.4	2.4	0.1	384
E169 (14.4%)	35.3	2.6	0.1	673
S1016	35.3	2.4	0.1	1611
E475 (15.01%)	35.3	2.8	0.1	162
E169 (14.4%)	35.1	2.6	0.14	673
E476	35.1	2.6	0.1	394
Griffith 30% Suction Airfoil	35	2.6	0.05	1824
GOE 775	35	2.2	0.1	907
NACA 63(3)-018	34.9	2.6	0.1	1687
NACA 0021	34.8	2.2	0.1	1713
EPPLER 473	34.7	2.8	0.1	424
E474 (14.09%)	34.7	2.6	0.1	237
S1048 14% (Danny Howell)	34.7	2.2	0.19	618
GOE 460	34.6	2	0.1	1340
S1014	34.4	2.6	0.1	1612
FX LIII-142 K 25	34.3	2.4	0.14	1850
NACA 0012 S	34.2	2.2	0.19	1743
US1000ROOT	34.2	2.8	0.1	1594
naca-0014	34.2	2.4	0.14	271
E168 (12.45%)	34.2	2.2	0.19	1215
E168 (12.45%)	34.1	2.4	0.14	1215
GOE 410	34.1	2.6	0.1	215
GOE 776	34	3	0.05	186
NACA 16-021	34	2.8	0.1	1703
NACA 0024	34	3	0.05	1712

-- Edited by brother paul on Sunday 12th of February 2012 01:07:41 PM

__________________

windgen.org vawt discussion