1.3+ is important and will vary based on design because the supersonic wave drag is only overcome after around ~1.3 mach for conventional designs and maybe 1.2 for a highly optimized design (impossible for a fighter aircraft, maybe for a missile).
The R-77 for example overcomes wave drag around 1.3 mach, which is why I pose that as a “safe number” for a fighter.
TL;DR overcoming supersonic wave drag means thrust can then be reduced and it improves the economy of supersonic cruise.
For higher speeds like 700kph 6.4 and 6.14 are more similar, the problems are at lower speeds:
n_y = \dfrac{\dfrac{1}{2}\ ρ \ Cl \ A (\dfrac{V_{tas}}{3.6})^2 +\sin{(α+φ)}\ 2T\ g }{m\ g}
N_y = n_y \,\cos{α}
m = 13000kg
h = 1000m
V_{ias} = 500kph
V_{tas} = 528kph
ρ at 1000m = 1.112
A = 38m^2
α = 24 degrees
Cl at 24 degrees AoA = 1.42
Thrust (kg) at 1000m and 500kph IAS is ~ 6850kgf
φ = 5 degrees
g = 9.81m/s^2
With this datas for 1000m, 500kph and 24 degrees AoA we get N_y = 5G pull, which is what 6.14 indicates.
According to 6.4 the aircraft is turning at N_y = 5g at the same 500kph ias with less angle of attack, which is impossible without more thrust and especially lower weight.
Why are you transferring from a linked system if there’s a high-speed one everywhere in the book?
In 6.4, the TAS speed will be 550km/h.
Because 6.14 uses Ny, which is also what the MiG-29 G meter uses and what is used in the local host.
If 6.14 was ny the aircraft would turn much worse than it does right now.
yes but ρ decreases to 1.007, leading to a little worse turn overall for the same angle of attack, which is to be expected since altitude increases. Still the higher TAS and lower density somewhat compensate for each other, especially since it’s only 1000m.
is there any mention of it in the manual/any thrust figures? Because the values the current MiG-29 is based on the thrust chart 5.4, if there are modes that let it exceed that thrust they should be implemented
The Ny that is being used is shown on the device is not equal to that in the local system. It is calculated from the formula embedded in the block of linear accelerations. And all the graphs in the book are given for the velocity coordinate system.
“Двигатель 88 Руководство по технической эксплуатации Книга 1”
It’s not a secret
At first that’s what I had understood as well, but at least chart 6.14 is certainly for the local system, calculations match for every speed calculating n_y (velocity system) from polars and thrust and then multiplying it by cos(AoA) like I did above.
I’ve also re tested the flight model in game (I am sure the local host uses N_y (local system) since turn time matches with t = \dfrac{2π}{g} \dfrac{V_tas}{\sqrt{\left(\dfrac{N_y}{\cos(AoA)}\right)^2-1}} and not t = \dfrac{2π}{g} \dfrac{V_tas}{\sqrt{\left(N_y\right)^2-1}}
at 400, 450 and 500kph IAS and the results match calculations from polars (charts 2.2, 2.13) and thrust (chart 5.4).
Do you have a copy of the manual? If so we should report the missing engine mode, since reliability is not a concern in war thunder
What manual is this from?
Why M29 have such low acceleration at altitude?
Why is the first polar different than this one?
Are there further mentions of the RPT mode? Because I think we need thrust values to have any hopes of it being implemented, I don’t know how gaijin would estimate thrust with 1.5% extra foam
because there is a polar from another aircraft and it is shown for training purposes. On the left are the poles of the velocity coordinate system. On the right, as you can see, the Cx is negative here
oh ok so it is not a polar for the MiG-29.
Was any previous bug report written about the missing engine mode?
