Aces High Bulletin Board
General Forums => Aircraft and Vehicles => Topic started by: F4UDOA on January 30, 2004, 10:53:34 AM
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I will start this post off by just showing the English translation of the La-7 VVS flight test. I am highlighting the part that clearly shows the fuel consumption at sea level and the top speed clearly matches HTC's charts at 357MPH at MIL power.
This shows the duration at Mil power being 35 minutes. In the MA this would yield a duration of 17.5minutes and currently I believe it is 27minutes. Also at the next altitude of 3,000meters duration drops to 33 minutes.
The rest of th test including WEP test are in the next post. There are no WEP fuel consumtpions listed.
Fund of NII VVS, inv. 485716, file 273
Approved. Chief Engineer of VVS A.Repin, 11 Oct 1944
THE STATEMENT
on results of verification trials of a serial La-7 with ASh-82FN engine and
VISh-105V-4 propeller, D=3.1m
/ac.No 45210203, prod. in July 1944 by factory No 21/
Air combat with Me-109G-4
In horizontal manoeuvring up to 5000m the La-7 gets on the tail of
the Me-109 for an aimed shot after 3-4 turns. Above 5000 m the advantage of
La-7 in horizontal manoeuvre decreases. At an altitude of 7000m horizontal
manoeuverability of both planes is equal.
In vertical manoeuvring the La-7 has an obvious advantage over the Me-109
up to 3500m and can keep an altitude dominance of 150m during combat. When
it reaches an altitude of 3500m the La-7 slightly loses its superiority over
the Me-109 in vertical manoeuverability, but even at 7000m the La-7 can
maintain a dominance of about 40-50m. At 6500-7000m the vertical
manoeuverability of both planes is equal.
The La-7 accelerates into the dive faster than the Me-109 and therefore can
reduce the distance to an escaping target. However, in continuous dive the
Me-109 increases its speed faster after initial acceleration and departs from
the La-7.
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========================page02.gif======================================
Approved. 1st Deputy Chief of GK NII VVS Losyukov. 6 Jan 1945.
REPORT No 2
on results of flight trials for fuel consumption and range measurements
of La-7 No38103254 with ASh-82FN engine and VISh-105V-4 propeller.
The object of research
La-7 No 38103254 produced by plant No 381... Total weight 3265 kg, fuel tanks
capacity - 460 litres. The landing-gear and the tail wheel were up,
the canopy was closed, the cap of oil-cooler and the skirt of engine cowl
were set "along the flood" (feathered).
The results of the tests.
The measurements of fuel consumption with working engine had been carried
out on the ground and during a climb at max climb rate. As a result it has
been established that fuel consumption of a working engine is 2.35 l/min
on the ground (during warm-up and engine test, taxiing to and from the
starting position).
Fuel consumption at climb to H at maximum climb rate mode, in litres
n=2400RPM
H,m 1000 2000 3000 4000 5000 6000 7000
Q,litres 15 25 35 45 55 65 80
IAS, km/h 270 270 270 265 260 255 250
Chart of range and level flight duration of a/c La-7 No38103254 at different
flight modes at V/n=const (constant speed and RPM), G tot=3265kg (total
weight) and V fuel=460 l (fuel volume)
n, Supercharg. Speed, km/h q, Qf, Till the dry tank:
RPM pressure, IAS TAS lit./km lit./h Range of Level flight
mm of merc. level flight, duration,
pile km h-min
H=1000m (1st speed of supercharger), fuel supply for level flight - 365 l
2400 1020 575 608 1.020 620 355 0-35
2200 875 530 560 0.800 448 455 0-49
2000 745 480 508 0.655 333 555 1-06
1800 665 430 455 0.585 266 625 1-22
1600 610 385 407 0.560 228 650 1-36
1500 580 360 380 0.550 209 665 1-45
H=3000m (1st speed of supercharger), fuel supply for level flight - 345 l
2400 990 554 644 0.975 628 355 0-33
2200 830 510 588 0.745 438 460 0-47
2000 705 460 532 0.620 330 555 1-03
1800 615 415 480 0.575 276 600 1-15
1600 560 370 428 0.555 238 620 1-27
1500 545 345 400 0.550 220 625 1-34
H=5000m (2nd speed of supercharger), fuel supply for level flight - 325 l
2400 1020 513 658 0.910 600 355 0-32
2200 840 470 604 0.700 423 465 0-46
2000 720 430 554 0.600 333 540 0-58
1800 630 385 496 0.560 278 580 1-10
1600 590 340 440 0.550 242 590 1-20
H=7000m (2nd speed of supercharger), fuel supply for level flight - 300 l
2400 870 454 647 0.735 476 405 0-38
2200 685 415 593 0.570 338 525 0-53
2000 590 380 544 0.500 272 600 1-06
1800 515 340 490 0.460 225 650 1-20
1600 465 300 433 0.450 195 665 1-32
Notes:
1. For range and flight duration calculations the following fuel consumptions
are taken into account:
========================page03.gif======================================
a) for engine work on the ground (warming-up and engine test, taxiing to and
from the start) 35 l per 15 min;
b) for climb to: 1000m - 15 l; 3000 m - 55 l; 7000 m - 80 l;
c) for circle flight before landing - 45 l.
2. To obtain the values of technical range and flight duration add the
following range and time figures to the table values respectively:
1000m - 5km, 1 min
3000m - 15km, 3 min
5000m - 25km, 5 min
7000m - 40km, 8 min
The table of range and flight duration for La-7 No 38103254 with
G full=3265kg, full tank fuel supply - 460 l.
Mode Mode values Level flight
up to dry tanks:
Range, km duration,
h-min
Max. H=1000m(1st sup.sp.),n=2400, Ps=1020mm Me.pl. 355 0-35
speed 3000 1 2400 990 355 0-33
5000 2 2400 1020 355 0-32
7000 2 2400 870 405 0-38
Fast H=1000m(1st sup.sp.),n=2160, IAS=518 km/h 485 0-53
range 3000 1 2160 498 490 0-51
(0.9 5000 2 2160 462 485 0-49
Vmax) 7000 2 2160 408 545 0-56
Near H=5000m(2nd sup.sp.),n=1810, IAS=388 km/h 580 1-10
fast range TAS=500 km/h
Optim. H=1000m(1st sup.sp.),n=1500, IAS=360 km/h 665 1-45
mode 3000 1 1500 345 625 1-34
5000 2 1600 340 590 1-20
7000 2 1600 300 665 1-32
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Approved. Chief engineer of VVS A.Repin, 21 Jun 45
The statement No 112
on results of verification trials of La-7 serial plane with ASh-82FN engine
and VISh-105V-4 propeller D=3.1m, equipped with hydraulically controlled
dust filter and new ventilation of cockpit
/ a/c No 45213276, plant No 21, prod. of April 1945 /
Table of max. horizontal speeds
H standard, TAS, km/h
m nominmal, n=2400 RPM WEP, n=2500 RPM
0 580 616
1000 604 639
2000 626 661
2200 1) - 666
3000 649 657
3250 2) 654 654
4000 645 -
5000 651 -
6000 672 -
6250 3) 677 -
7000 666 -
8000 651 -
1) - 1st altitude boundary with WEP
2) - 1st altitude boundary without WEP
3) - 2nd altitude boundary without WEP
Table of max. climb rates
H st., m Vy (vert. speed), m/s Time, min IAS, km/h
nominal WEP nominal WEP
0 20 24.2 0 0 264
1000 20 24.2 0.85 0.65 259
1600 1) - 24.2 - 1 -
2000 20 - 1.7 1.3 253
2650 2) 20 - - - -
3000 18.6 - 2.6 2.2 246
4000 15 - 3.55 3.2 239
5000 15 - 4.65 4.3 232
5100 3) 15 - 4.75 4.4 -
6000 12.7 - 5.9 5.45 224
7000 10.2 - 7.4 - 214
8000 7.6 - 9.3 - 204
9000 5 - 12.0 - 189
10000 2.4 - 16.6 - 166
10750 4) 0.5 - 26.0 - -
1) - 1st altitude boundary with WEP
2) - 1st altitude boundary without WEP
3) - 2nd altitude boundary
4) - practical ceiling
========================page05.gif======================================
Maneuverability (nominal/WEP)
BFM Init.IAS, km/h Result.IAS, km/h Time, sec. Change of alt., m
1000m 5000m 1000m 5000m 1000m 5000m 1000m 5000m
360deg. turn:
- left 340 300 340 300 19.5 27 0 0
- right 340 300 340 300 18.5 26 0 0
Combat turn:
- left 550/580 470 270 260 17 15 1100/1300 850
- right 550/580 470 270 260 17 15 1100/1300 850
Split-S (overturn, upheaval):
- left - 260 - 380 - - - 800
- right - 260 - 380 - - - 800
Take-off capabilities
Flaps Weight, n, P superch. Take-off Time, Take-off Take-off dist.
kg RPM mm of Me pile run, m s speed, km/h m
Retrct. 3275 2400 1000 380 14.2 175 1000
Retrct. 3275 2500 1120 335 12.7 175 880
Landing capabilities
Flaps Brakes Weight, Landing Time, Landing Landing dist.
usage kg run, m s speed, km/h m
Full Used 3035 440 17.9 135 1000
*) Take-off and landing distances are for 25m high obstractles.
Range and flight duration for weight of 3275kg and 328kg(445 l) of fuel.
Mode Altitude,m Speed,km/h n,RPM P sup, Till dry tanks:
indic. stand. IAS TAS mm Me.pl. tech. tech.flight
range,km dur., h-min
Max. 1000 1020 358 376 1500 620 635 1-41
range
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========================page06.gif======================================
Approved. Chief engineer of VVS A.Repin, 29 Dec 45
The statement No 222
on results of verification trials of La-7 with ASh-82FN engine and VISh-105V-4
propeller in order to determine manoeuverability characteristics
/ a/c No 38100869, plant No 381, prod. of July 1945 /
Lead pilots: major Kubyshkin A.G., captain Pikulenko D.G.
Brief data
The complete verification trials were to determine the difference between right
and left manoeuvres and influence of the engine mode on manoeuverability
characteristics (360deg. turns at 1000 and 5000m, combat turns and split-Ss)
are to be done for the first time.
The plane has been tested with normal flight weight of 3310kg at nominal
engine mode (Ps=1000mm of Me. pile, n=2400RPM).
Conclusion.
1. La-7 does manoeuvres better backward to propeller rotation's direction,
as well as Yak-3.
2. The difference between right and left manoeuvres for La-7 is less than
for Yak-3 (the difference in time of right and left turns is 0.3-0.7 sec
for La-7 and 1.0 sec for Yak-3).
Inferences.
1. La-7 No 38100869 has following manoeuverability characteristics:
a) optimum extreme sustained turn
H, m Direction IAS,km/h Time,sec Radius,m Bank angle,deg.
1000 right 320-340 21.0-21.2 305-335 70.7-71.4
left 320-340 20.7-21.0 290-315 71.2-71.5
5000 right 280-290 30.7 485-500 64.3-64.8
left 280-290 30.0 470-490 65.4-65.7
b) combat turn
Init. Direction Init. result. Alt.gained,m Time,sec
H, m IAS,km/h IAS,km/h
1000 right 560 270 1170 24
left 560 270 1170 24
5000 right 460 240 930 23
left 460 240 950 23
c) split-S
Init. Direction Init. result. Alt.loss,m Time,sec
H, m IAS,km/h IAS,km/h
2000 right 235 350 595 13
left 235 345 575 13
5000 right 225 350 820 16
left 225 340 790 15
2. The characteristics of optimum multiple (sustained) 360deg. turns obtained
of both the pilots are practically identical (the differences are in
admissible limits).
3. The combat turns' characteristics at H=1000 m obtained by both pilots
are practically identical.
4. The combat turns' characteristics at H=1000 m obtained by both pilots
are slightly different in gained altitude. The altitude addition obtained
by each pilot differs from mean turn in +20-25m. Such a difference should
be considered as the standard accuracy of climb definition at H=5000.
5. The split-S data obtained by both pilots are slightly different
in altitude loss, the time to perform and resulting speed. The altitude
loss obtained by each pilot differs from mean result in +20-25m. Time of
manoeuvres are different from the mean value by 1 sec, and the difference
in resulting speeds is 10 km/h IAS. Such a difference should be considered
as the standard accuracy of split-s data definition at H=2000 and 5000m.
6. Manoeuvres, performed in direction opposite to propeller rotation
(left for La-7), are better than ones performed in other direction.
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diagr01.gif
*** Diagram: "La-7 N 45210139 (verification trials in LII NKAP)"
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========================page08.gif======================================
*** Diagram: "La-7 N 45213276 (verification trials in GK NII VVS)"
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========================page09.gif======================================
Basic flight-technical data of serial piston engined fighters La-7 1944-1945.
Aircraft, engine, dates of start and end of trials.
1. Flight weight, kg
2. Wing loading, kg/m2
3. Take-off power loading, kg/H.P.
4. Fuel supply, litres
5. Max level speed:
- at deck level (nominal/WEP), km/h
- at 1st altitude boundary (nominal/WEP), km/h / m
- at 2nd altitude boundary, km/h / m
6. Climb time to 5000m (nominal/WEP), min
7. Climb rate at deck level (nominal/WEP), m/s
8. Practical ceiling, m
9. Maximum range, km:
- at H=1000m
- at H=3000m
- at H=5000m
- at H=7000m
- comparative fast range
(H=5000m, TAS=500km/h)
10. Flight duration at max range mode, hour-min:
- at H=1000m
- at H=3000m
- at H=5000m
- at H=7000m
- comparative fast range
(H=5000m, TAS=500km/h)
11. 360deg. turn time, s:
- at H=1000m
- at H=5000m
12. Altitude addition per combat turn, m:
- from H=1000m
- from H=5000m
13. Take-off run/distance (nom./WEP), m
14. Landing run/distance, m
15. Landing speed, km/h
16. Armament, No. x caliber/ammunition load
17. Geometrical data (sizes):
- overall length, m
- wingspan, m
- wing area, m2
- wing profile
- horizontal empennage area, m2
- vertical empennage area, m2
- chassis rut (transversal distance between wheels), m
Notes:
1) Serial La-7 No 45210150, plant No21, prod. of July 1944, verification trials
in GK NII VVS.
2) The same plane after governor RS-2 tuning, standard propeller mounting,
improvement of fuselage and cowl sealing, improvement of external
finishing; trials in LII NKAP.
3) Serial La-7 No 45210203, plant No21, prod. of July 1944, verification trials
in GK NII VVS.
4) Serial La-7 No 38103254, plant No381, trials for fuel consumption in
GK NII VVS.
5) Serial La-7 No 38105260, plant No381, trials for fuel consumption in
GK NII VVS.
6) Serial La-7 No 45213276, plant No21, prod. of April 1945, verification trials
in GK NII VVS.
7) Serial La-7 No 38102663, plant No381, prod. of May 1945, verification trials
in GK NII VVS.
8) Serial La-7 No 38100869, plant No381, prod. of July 1945, verification trials
for manoeuverability in GK NII VVS.
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F4UDOA, for the last 3 days pyro and I have been working on a new fuel consumption model. So thing will be changing a lot.
HiTech
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wtg HT I think corellating the rpm and throttle to achieve the full range of manifold then matching fuel consumption to that (parabolic with a K factor for different AC) would be great. Plus you could then put rpm based WEP on that calculation and leave the seperate button to the additve WEP.
Then you have a full fuel model (including WEP which of course will add another problem of limiting its time.........but you guys can do it!)
I edited the column headers to make them clearer.........I hope
Edit columns
man =mm mercury
IAS & TAS = Km/hr
range =km
time = hours - minutes
rpm man IAS TAS L/km l/hr range time
H=1000m (1st speed of supercharger), fuel supply for level flight - 365 l
2400 1020 575 608 1.020 620 355 0-35
2200 875 530 560 0.800 448 455 0-49
2000 745 480 508 0.655 333 555 1-06
1800 665 430 455 0.585 266 625 1-22
1600 610 385 407 0.560 228 650 1-36
1500 580 360 380 0.550 209 665 1-45
H=3000m (1st speed of supercharger), fuel supply for level flight - 345 l
2400 990 554 644 0.975 628 355 0-33
2200 830 510 588 0.745 438 460 0-47
2000 705 460 532 0.620 330 555 1-03
1800 615 415 480 0.575 276 600 1-15
1600 560 370 428 0.555 238 620 1-27
1500 545 345 400 0.550 220 625 1-34
H=5000m (2nd speed of supercharger), fuel supply for level flight - 325 l
2400 1020 513 658 0.910 600 355 0-32
2200 840 470 604 0.700 423 465 0-46
2000 720 430 554 0.600 333 540 0-58
1800 630 385 496 0.560 278 580 1-10
1600 590 340 440 0.550 242 590 1-20
H=7000m (2nd speed of supercharger), fuel supply for level flight - 300 l
2400 870 454 647 0.735 476 405 0-38
2200 685 415 593 0.570 338 525 0-53
2000 590 380 544 0.500 272 600 1-06
1800 515 340 490 0.460 225 650 1-20
1600 465 300 433 0.450 195 665 1-32
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Very glad to hear this.
-Blogs
Originally posted by hitech
F4UDOA, for the last 3 days pyro and I have been working on a new fuel consumption model. So thing will be changing a lot.
HiTech
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This is tricky. As we have learned fuel mixtures depend a lot on carburetor/injector settings. We know what the ideal is, but we don't typically know what the fudge factor is to prevent detonation.
-Blogs
Originally posted by Tilt
wtg HT I think corellating the rpm and throttle to achieve the full range of manifold then matching fuel consumption to that (with a K factor for different AC) would be great. Plus you could then put rpm based WEP on that calculation and leave the seperate button to the additve WEP.
Then you have a full fuel model (including WEP which of course will add another problem of limiting its time.........but you guys can do it!)
I edited the column headers to make them clearer.........I hope
Edit columns
man =mm mercury
IAS & TAS = Km/hr
range =km
time = hours - minutes
rpm man IAS TAS L/km l/hr range time
H=1000m (1st speed of supercharger), fuel supply for level flight - 365 l
2400 1020 575 608 1.020 620 355 0-35
2200 875 530 560 0.800 448 455 0-49
2000 745 480 508 0.655 333 555 1-06
1800 665 430 455 0.585 266 625 1-22
1600 610 385 407 0.560 228 650 1-36
1500 580 360 380 0.550 209 665 1-45
H=3000m (1st speed of supercharger), fuel supply for level flight - 345 l
2400 990 554 644 0.975 628 355 0-33
2200 830 510 588 0.745 438 460 0-47
2000 705 460 532 0.620 330 555 1-03
1800 615 415 480 0.575 276 600 1-15
1600 560 370 428 0.555 238 620 1-27
1500 545 345 400 0.550 220 625 1-34
H=5000m (2nd speed of supercharger), fuel supply for level flight - 325 l
2400 1020 513 658 0.910 600 355 0-32
2200 840 470 604 0.700 423 465 0-46
2000 720 430 554 0.600 333 540 0-58
1800 630 385 496 0.560 278 580 1-10
1600 590 340 440 0.550 242 590 1-20
H=7000m (2nd speed of supercharger), fuel supply for level flight - 300 l
2400 870 454 647 0.735 476 405 0-38
2200 685 415 593 0.570 338 525 0-53
2000 590 380 544 0.500 272 600 1-06
1800 515 340 490 0.460 225 650 1-20
1600 465 300 433 0.450 195 665 1-32
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HT,
Thanks for listening:aok
I have been studying fuel consumption like a madman for a while now. I have emailed most of my docs to Pyro.
What I am posting now is as much for the comminuty as anything.
Again thanks for being responsive.
BTW, I will probably do one more consumption post on the BF109-G10/K4 and the DB-605ASC just to drive the Luftwabbles crazy.
Just ignore it, if it is old news.
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could some one tell me very simple how much was the range at cruise and full power of the LA7 in miles
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Originally posted by simshell
could some one tell me very simple how much was the range at cruise and full power of the LA7 in miles
Rough guide 1 km = 5/8mile
Full power no wep was at 2400 rpm
(eg at just under 10,000 ft @ 2400 rpm with man 990 on 1st stage boost it had a range of approx 222 miles)
You could assume cruise to be about 2000 rpm
(eg at just under 10,000 ft @ 2000 rpm with man 705 on 1st stage boost it had a range of approx 347 miles)
What is referred to as maximum range mode seems to give a range of 390 miles at rpm 1500 man 545 (half power).
However I am also aware that continued running at lowest revs gave concern re plugs oiling and fouling.
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btw page 9 is the translation of the text on some tables..............
I have the tables and for 2 AC the detail ranges are given and the max range and comparative fast ranges are given for three others...........
They vary.................
(http://www.tilt.clara.net/data/PAGE09.GIF)
(http://www.tilt.clara.net/data/PAGE10.GIF)
Serials starting 452 were most probably from Gorky........
Those starting 381 I would speculate were from tblisi as this was the only plant to produce the 3 gun variant later on.
You will note the significant difference in ranges which may be expected across such trials with ex production AC manufactured under mediocre quality control standards.
However it would be prudent to note that 381032534 (subject of more detailed data above). Was at the lower end of the group tested...........ie its endurance was less than average for the type.
Particularly when compared to 38105260 tested some 5 months later. (also it seems the subject of range tests although we do not know the rpm and manifold pressures for this later set of figures)
Note the cannon load outs for all these trials.
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The following is a chart I did a while back based on Tilt's translation of the La-7 flight test data.
Tilt - please correct me if there is something off here.
-blogs
(http://mysite.verizon.net/vze479py/sitebuildercontent/sitebuilderpictures/la7_table.gif)
Originally posted by simshell
could some one tell me very simple how much was the range at cruise and full power of the LA7 in miles
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WTG JoeB!!
I just saved you chart in my files. Question, where do you see TAS as 378MPH? I see the 357MPH at 3K but I'm not sure where the TAS number came from.
Tilt,
Great stuff once again. Do you have a translated copy of those pages??
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It should have come from transforming a TAS number from KM to miles, but I did that a year ago. I'll check the program.
-Blogs
Originally posted by F4UDOA
WTG JoeB!!
I just saved you chart in my files. Question, where do you see TAS as 378MPH? I see the 357MPH at 3K but I'm not sure where the TAS number came from.
Tilt,
Great stuff once again. Do you have a translated copy of those pages??