Airfoil: WASP Builder: M. Fox Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60700 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.30 -0.182 0.0292 0.0329 0.0252 0.0292 0.0296 -2.62 -0.046 0.0210 0.0200 0.0183 0.0229 0.0227 -1.00 0.104 0.0167 0.0145 0.0163 0.0124 0.0235 0.39 0.313 0.0207 0.0180 0.0233 0.0141 0.0275 2.00 0.550 0.0204 0.0175 0.0322 0.0115 0.0202 3.35 0.673 0.0220 0.0154 0.0337 0.0220 0.0167 4.94 0.809 0.0286 0.0155 0.0353 0.0416 0.0220 6.70 0.960 0.0334 0.0230 0.0437 0.0430 0.0240 8.15 1.079 0.0367 0.0350 0.0427 0.0384 0.0307 9.65 1.183 0.0346 0.0350 0.0338 0.0364 0.0331 11.26 1.263 0.0422 0.0400 0.0530 0.0368 0.0390 Tabulated from data in file AB00229.DAT & reduced using program Q01.00L Average Reynolds #: 101300 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -4.18 -0.206 0.0244 0.0253 0.0233 0.0251 0.0240 -2.44 -0.053 0.0190 0.0186 0.0201 0.0188 0.0187 -0.87 0.164 0.0125 0.0128 0.0125 0.0111 0.0137 0.24 0.342 0.0138 0.0132 0.0170 0.0128 0.0124 2.06 0.539 0.0150 0.0144 0.0154 0.0152 0.0148 3.64 0.683 0.0159 0.0171 0.0154 0.0159 0.0150 5.24 0.834 0.0176 0.0191 0.0175 0.0174 0.0164 7.09 1.007 0.0213 0.0215 0.0231 0.0206 0.0200 8.22 1.097 0.0240 0.0237 0.0260 0.0240 0.0222 9.90 1.220 0.0264 0.0277 0.0251 0.0273 0.0257 Tabulated from data in file AB00144.DAT & reduced using program Q01.00L Average Reynolds #: 201600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.03 -0.171 0.0181 0.0149 0.0175 0.0230 0.0170 -2.65 0.006 0.0129 0.0131 0.0141 0.0118 0.0127 -0.29 0.285 0.0088 0.0081 0.0096 0.0091 0.0084 0.41 0.352 0.0091 0.0088 0.0099 0.0090 0.0085 2.63 0.586 0.0108 0.0109 0.0104 0.0105 0.0114 3.51 0.675 0.0115 0.0122 0.0107 0.0109 0.0121 5.13 0.834 0.0134 0.0139 0.0118 0.0142 0.0136 6.65 0.979 0.0155 0.0160 0.0147 0.0155 0.0158 8.28 1.120 0.0182 0.0189 0.0174 0.0185 0.0179 9.81 1.215 0.0242 0.0257 0.0266 0.0220 0.0225 11.11 1.245 0.0353 0.0396 0.0361 0.0294 0.0362 Tabulated from data in file AB00231.DAT & reduced using program Q01.00L Average Reynolds #: 302600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.31 -0.172 0.0154 0.0152 0.0133 0.0164 0.0166 -2.53 0.048 0.0107 0.0099 0.0104 0.0115 0.0108 -1.02 0.198 0.0087 0.0077 0.0090 0.0091 0.0088 0.90 0.397 0.0081 0.0077 0.0077 0.0087 0.0082 2.23 0.541 0.0090 0.0089 0.0086 0.0087 0.0096 3.61 0.680 0.0099 0.0102 0.0089 0.0098 0.0106 5.07 0.826 0.0115 0.0118 0.0101 0.0119 0.0121 6.48 0.964 0.0130 0.0134 0.0119 0.0133 0.0133 8.13 1.108 0.0156 0.0159 0.0151 0.0155 0.0160 9.53 1.204 0.0204 0.0204 0.0231 0.0184 0.0195 11.27 1.249 0.0339 0.0395 0.0361 0.0267 0.0332 Tabulated from data in file AB00233.DAT & reduced using program Q01.00L File wasp.drg created on 12-05-1997 at 15:26:00 using program FORMAT