cathar1244 > RE: Determining fixed wing aircraft AA and DF values (4/7/2019 11:39:36 AM)

Step 5  assess airframe performance Submethod: Airframe assessment. a. Divide the service ceiling in feet by 10,000. (Ab) b. Divide the maximum speed in mph by 66.667. (Ac) c. Divide the wing loading in pounds per square feet by 10. (Ad) d. Multiply the mph per ton of loaded aircraft by the construction modifier (see Step 2). e. Divide this adjusted mph per ton of loaded aircraft by 18. (Ae) f. Determine a factor in the range 1 to 10 for the effectiveness of avionics etc. (Af) g. If crew is more than 1, the crew factor (Ag) is equal to 1.2, else it is equal to 1. The raw airframe assessment is calculated as: ( Ab + Ac  Ad + Ae + Af ) * Ag This raw assessment is then multiplied by the design modifier (see Step 2): AA = (raw_assessment * design_modifier) Example. An F16C has a service ceiling of 52,450 feet. Ab is then 5.245. The maximum speed is given as 1,320 mph, so Ac is 19.80. Wing loading is 88.3 pounds per square foot, so Ad is 8.83. Avionics, fire control, and onboard radar are assessed as 7. Crew is 1, so Ag is equal to 1. The mph per (2000pound) ton of loaded aircraft is 87.67. This is adjusted by the construction factor of 0.88 (1970s era design). The adjusted mph per ton of loaded aircraft is 77.15. This adjusted figure is divided by 18, setting Ae to 4.29. Raw score is ( 5.245 + 19.8  8.83 + 4.29 + 7 ) * 1, or 27.51 AA = 27.51 * 1 (the design modifier), or 27.51 To the value of AA must be added the weapons effectiveness. Assuming this F16 is equipped with the NR30 cannon, the antiair value is: 27.51 + 6.33, or 33.84  this rounds to 34.



