(2) 2.0 VSO, where VSO is the computed stalling speed with wing flaps fully extended at the maximum weight. 5.2.4.3 Design Cruising Speed, VC 4.6 – (1) VC in knots may not be less than and 4.77 x √(W/S); (2) VC need not be greater than 0.9 VH at sea level. 5.2.4.4 Design Dive Speed, VD: 4.7 VD = 1.4 x VC min where: VC min = required minimum cruising speed. 5.2.5 Limit Maneuvering Load Factors: – 5.2.5.1 The positive limit maneuvering load factor n1 may not be less 6 than 4.0. 5.2.5.2 The negative limit manouevring load factor n2 may not be 6 greater than −2.0. 5.2.5.3 Loads with wing flaps extended: 6 (1) if flaps or other similar high lift devices are used, the airplane must be designed for n1 = 2.0 with the flaps in any position up to VF; and (2) n2 = 0. 5.2.5.4 Loads with speed control devices: Not applicable 5.2.6 Gust Load Factors The airplane must be designed for the 6.1 – 5.2.6.1 loads resulting from: 5.2.6.2 The gust velocities specified in 5.2.3.3 with flaps retracted, and positive and negative gusts of 7.5 m/s (24.6 ft/s) nominal intensity at VF with the flaps fully extended. NOTE 4 In the absence of a more rational analysis, the gust – load factors may be computed by the method of Appendix X3. Table 1 – Requirements Design Airspeeds This chapter defines the operating and design airspeeds as required for certification . Maximum speed in level flight VH According to flight tests at maximum weight and maximum continuous power at sea level conditions, the maximum speed in level flight has been determined: Stall speeds VS, VS0, VS1 These speeds will be verified by flight test according to requirement 4.4.1 . In order to calculate the stall speed, the maximum lift coefficient of the aeroplane as a whole is determined first.
(2) 2.0 VSO, where VSO is the computed stalling speed with wing flaps fully extended at the maximum weight. 5.2.4.3 Design Cruising Speed, VC – (1) VC in knots may not be less than 4.77 x √(W/S); and (2) VC need not be greater than 0.9 VH at sea level. 4.6 5.2.4.4 Design Dive Speed, VD: VD = 1.4 x VC min where: VC min = required minimum cruising speed. 4.7 5.2.5 Limit Maneuvering Load Factors: – 5.2.5.1 The positive limit maneuvering load factor n1 may not be less than 4.0. 6 5.2.5.2 The negative limit manouevring load factor n2 may not be greater than −2.0. 6 5.2.5.3 Loads with wing flaps extended: (1) if flaps or other similar high lift devices are used, the airplane must be designed for n1 = 2.0 with the flaps in any position up to VF; and (2) n2 = 0. 6 5.2.5.4 Loads with speed control devices: Not applicable 5.2.6 5.2.6.1 5.2.6.2 Gust Load Factors – The airplane must be designed for the loads resulting from: The gust velocities specified in 5.2.3.3 with flaps retracted, and positive and negative gusts of 7.5 m/s (24.6 ft/s) nominal intensity at VF with the flaps fully extended. NOTE 4 – In the absence of a more rational analysis, the gust load factors may be computed by the method of Appendix X3. 6.1 Table 1 – Requirements Design Airspeeds This chapter defines the operating and design airspeeds as required for certification . Maximum speed in level flight VH According to flight tests at maximum weight and maximum continuous power at sea level conditions, the maximum speed in level flight has been determined: Stall speeds VS, VS0, VS1 These speeds will be verified by flight test according to requirement 4.4.1 . In order to calculate the stall speed, the maximum lift coefficient of the aeroplane as a whole is determined first.
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