2.33.0.54 F111&그리펜,[빌카스 버프]

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워썬더, 인리스티드 등 가이진 퍼블리싱 게임 채널

워썬더 소식 2.33.0.54 F111&그리펜,[빌카스 버프]

LITTORIO

추천 5 비추천 0 댓글 15 조회수 1587 작성일 2023-12-27 22:28:27

https://arca.live/b/gaijin/95153128

# 2.33.0.48 -> 2.33.0.50

* New Language : Vietnamese

# 2.33.0.50 -> 2.33.0.52

* Client Stability Improved

# 2.33.0.52 -> 2.33.0.53

* F-111A :
* Wing at 0% sweep
    * Oswald’s efficiency number reduced from 0.78 to 0.62
      * This will mean a higher coefficient of drag depending on AoA, reducing overall turn
    * Lift coefficient after critical AoA reduced from 1.2 to 1.05
      * Reduced lift after stall
    * Coefficient of drag Mach multiplier curve Critical Mach number from 0.78 to 0.74
      * Multiplier will begin applying from M0.74, resulting in slightly increased drag
    * Auxiliary Mach multiplier curve multiplier maximum reduced from 1.15 to 1.05
      * Slightly reduced coefficient of lift from M0.3 to M0.6
    * Induced drag Mach multiplier curve critical Mach number from 0.78 to 0.45
      * Induced drag multiplier will begin applying from M0.45 instead of M0.78, resulting in increased induced drag
    * Coefficient of lift at critical AoA reduced from 1.52 to 1.42
      * Reduced lift at critical AoA
* Wing at 0% sweep, flaps out
    * Oswald’s efficiency number reduced from 0.78 to 0.62
      * This will mean a higher coefficient of drag depending on AoA, reducing overall turn
    * Auxiliary Mach multiplier curve multiplier maximum reduced from 1.15 to 1.05
      * Slightly reduced coefficient of lift from M0.3 to M0.6
    * Induced drag Mach multiplier curve critical Mach number from 0.78 to 0.45
      * Induced drag multiplier will begin applying from M0.45 instead of M0.78, resulting in increased induced drag at lower speeds than before
* Wing at 50% sweep
    * Oswald’s efficiency number reduced from 0.71 to 0.54
      * This will mean a higher coefficient of drag depending on AoA, reducing overall turn
    * Lift coefficient after critical AoA increased from 0.8 to 0.95
      * Increased lift after stall
    * Induced drag Mach multiplier curve adjustments
* * * * Critical Mach number from 0.78 to 0.5
       * Coefficient max value from 1.05 to 1.1
       * Induced drag multiplier will begin applying from M0.5 instead of M0.78 and overall have slightly more induced drag both at lower speeds and overall
    * Zero-lift drag coefficient increased from 0.0073 to 0.0079
       * More overall drag
* Wing at 50% sweep, flaps out
    * Oswald’s efficiency number reduced from 0.7 to 0.54
      * This will mean a higher coefficient of drag depending on AoA, reducing overall turn
    * Lift coefficient after critical AoA decreased from 1.35 to 1.05
      * Reduced lift after stall
    * Induced drag Mach multiplier curve adjustments
      * Critical Mach number from 0.78 to 0.5
      * Coefficient max value from 1.05 to 1.1
      * Induced drag multiplier will begin applying from M0.5 instead of M0.78 and overall have slightly more induced drag both at lower speeds and overall
* Wing at 100% sweep
    * Oswald’s efficiency number reduced from 0.61 to 0.5
      * This will mean a higher coefficient of drag depending on AoA, reducing overall turn
    * Induced drag Mach multiplier curve adjustments
      * Critical Mach number from 0.78 to 0.5
      * Coefficient max value from 1.05 to 1.1
      * Induced drag multiplier will begin applying from M0.5 instead of M0.78 and overall have slightly more induced drag both at lower speeds and overall
    * Lift coefficient at critical AoA adjustments
      * High: 1.15 to 1.05
      * Low: -1.05 to -0.95
      * Slightly less lift at critical AoA, slightly more at negative critical AoA
    * Zero-lift drag coefficient reduced from 0.008 to 0.0077
      * Less overall drag
* Wing at 100% sweep, flaps out
    * Oswald’s efficiency number reduced from 0.61 to 0.5
      * This will mean a higher coefficient of drag depending on AoA, reducing overall turn
    * Induced drag Mach multiplier curve adjustments
* * * * Critical Mach number from 0.78 to 0.5
       * Coefficient max value from 1.05 to 1.1
       * Induced drag multiplier will begin applying from M0.5 instead of M0.78 and overall have slightly more induced drag both at lower speeds and overall
* Thrust maximum number before calculation reduced from 4940 to 4400 kgf
    * After calculation, this will express in a loss of around 1000-3000 kgf overall at any speed

* IL-2M (1943) : Enabled canopy control

* JAS39A, JAS39C :
* Wing
    * Oswald’s efficiency number increased from 0.52 to 0.53
      * This will mean a very slightly lower coefficient of drag depending on AoA, increasing overall turn
    * Coefficient of drag Mach multiplier curve adjustments
      * Critical Mach number from 0.9 to 0.92
      * Coefficient max value from 1.6 to 1.55
      * Multiplier will begin applying a tad bit later at M0.92 and overall have a bit less drag from M0.92 to M1.03 than previously
    * Induced drag Mach multiplier curve adjustments
      * Critical Mach number from 0.3 to 0.25
      * Coefficient max value from 0.88 to 0.78
      * Multiplier will begin applying from M0.25 instead of M0.3 and overall will have slightly more induced drag from M0.25 to M0.6
    * Zero-lift drag coefficient reduction from 0.008 to 0.0068
      * Overall less drag
* Wing with flaps out
    * Oswald’s efficiency number increased from 0.52 to 0.53
      * This will mean a very slightly lower coefficient of drag depending on AoA, increasing overall turn
    * Coefficient of drag Mach multiplier curve adjustments
      * Critical Mach number from 0.9 to 0.92
      * Coefficient max value from 1.6 to 1.55
      * Multiplier will begin applying a tad bit later at M0.92 and overall have a bit less drag from M0.92 to M1.03 than previously
    * Induced drag Mach multiplier curve adjustments
      * Critical Mach number from 0.3 to 0.25
      * Coefficient max value from 0.88 to 0.78
* * * * Multiplier will begin applying from M0.25 instead of M0.3 and overall will have slightly more induced drag from M0.25 to M0.6
    * Zero-lift drag coefficient reduction from 0.021 to 0.018
       * Overall less drag
* Fuselage
    * Coefficient of drag Mach multiplier curve coefficient max from 2.45 to 2.25
      * Lower drag multiplier from M0.92 to M1.05
    * Zero-lift drag coefficient reduction from 0.0061 to 0.0044
      * Overall less drag
* Very slightly increased elevator deflection at 2000 m from 1000-1900 km/h TAS
* Peak thrust changes
    * Thrust maximum number before calculation increased from 5100 to 5340 kgf
      * Only really matters for really really high altitudes because most of the thrust curve has been adjusted
    * At 0 m, 0-2000 km/h TAS
      * At 0 km/h from 7500 kgf to 8080 kgf
      * At 250 km/h from 7320 kgf to 8040 kgf
      * At 500 km/h from 7780 kgf to 8200 kgf
      * At 750 km/h from 8950 kgf to 8840 kgf
      * At 1000 km/h from 10125 kgf to 9140 kgf
      * At 1250 km/h from 10900 kgf to 8940 kgf
      * At 1500 km/h from 10800 kgf to 8050 kgf
      * At 1750 km/h from 9800 kgf to 8070 kgf
      * At 2000 km/h from 9030 kgf to 8090 kgf
    * At 3000 m, 250-2000 km/h TAS
      * At 250 km/h from 6370 kgf to 6700 kgf
      * At 500 km/h from 6580 kgf to 6880 kgf
      * At 750 km/h from 7250 kgf to 7100 kgf
      * At 1000 km/h from 8110 kgf to 7820 kgf
      * At 1250 km/h from 8900 kgf to 8840 kgf
      * At 1500 km/h from 9500 kgf to 8830 kgf
      * At 1750 km/h from 9600 kgf to 8700 kgf
      * At 2000 km/h from 9250 kgf to 8550 kgf
* * * At 6000 m, 250-2000 km/h TAS
       * At 250 km/h from 5160 kgf to 5350 kgf
       * At 500 km/h from 5550 kgf to 5500 kgf
       * At 750 km/h from 6060 kgf to 5860 kgf
       * At 1000 km/h from 6550 kgf to 6300 kgf
       * At 1250 km/h from 7200 kgf to 6830 kgf
       * At 1500 km/h from 7680 kgf to 7500 kgf
       * At 1750 km/h from 8080 kgf to 8400 kgf
       * At 2000 km/h from 7950 kgf to 8970 kgf
    * At 9000 m, 0-2000 km/h TAS
       * At 0 km/h from 3760 kgf to 3950 kgf
       * At 250 km/h from 3910 kgf to 3900 kgf
       * At 500 km/h from 4220 kgf to 4090 kgf
       * At 750 km/h from 4550 kgf to 4310 kgf
       * At 1000 km/h from 4930 kgf to 4750 kgf
       * At 1250 km/h from 5500 kgf to 5320 kgf
       * At 1500 km/h from 5880 kgf to 5750 kgf
       * At 1750 km/h from 6080 kgf to 6000 kgf
       * At 2000 km/h from 6080 kgf to 6130 kgf
    * At 12000 m, 0-2000 km/h TAS
       * At 0 km/h from 2400 kgf to 2180 kgf
       * At 250 km/h from 2560 kgf to 2140 kgf
       * At 500 km/h from 2870 kgf to 2200 kgf
       * At 750 km/h from 3200 kgf to 2360 kgf
       * At 1000 km/h from 3610 kgf to 2840 kgf
       * At 1250 km/h from 4000 kgf to 3500 kgf
       * At 1500 km/h from 4280 kgf to 4340 kgf
       * At 1750 km/h from 4430 kgf to 4980 kgf
       * At 2000 km/h from 4520 kgf to 5270 kgf
* Enabled center gear braking
* Autopilot max overload rate adjustment
    * From [-5, 13] to [-5, 16]
    * Will reach peak G slightly slower in a pull

# 2.33.0.53 -> 2.33.0.54

* Vilkas :
* Armor Rework
* Spike-LR2MR ATGM : Ammo Count : 2 -> 4

* New Texts :
* "Severe Damaged"

Current Dev version : 2.33.0.54
Current Live version : 2.33.0.52