Airfoil: CR-001 Builder: J. Robertson Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 59200 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.23 -0.107 0.0443 0.0437 0.0463 0.0446 0.0425 -2.70 0.062 0.0272 0.0271 0.0270 0.0280 0.0265 -1.16 0.217 0.0208 0.0232 0.0217 0.0190 0.0193 0.38 0.381 0.0215 0.0284 0.0207 0.0199 0.0172 1.82 0.562 0.0245 0.0235 0.0248 0.0252 0.0244 3.48 0.788 0.0297 0.0293 0.0311 0.0306 0.0280 5.01 0.975 0.0259 0.0246 0.0289 0.0255 0.0245 6.55 1.099 0.0264 0.0244 0.0255 0.0247 0.0310 8.08 1.202 0.0293 0.0302 0.0265 0.0300 0.0305 9.59 1.269 0.0385 0.0366 0.0362 0.0403 0.0410 11.10 1.318 0.0576 0.0587 0.0530 0.0605 0.0584 Tabulated from data in file CL00658.DAT & reduced using program Q02.00D Average Reynolds #: 99100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.25 -0.175 0.0488 0.0468 0.0485 0.0508 0.0493 -2.67 0.051 0.0237 0.0231 0.0233 0.0249 0.0235 -1.17 0.211 0.0194 0.0225 0.0181 0.0190 0.0181 0.39 0.429 0.0181 0.0182 0.0179 0.0180 0.0182 1.94 0.650 0.0211 0.0202 0.0223 0.0215 0.0203 3.49 0.829 0.0186 0.0165 0.0207 0.0192 0.0181 5.02 0.963 0.0173 0.0161 0.0186 0.0175 0.0171 6.56 1.089 0.0185 0.0178 0.0185 0.0191 0.0189 7.98 1.191 0.0250 0.0260 0.0233 0.0249 0.0258 9.59 1.266 0.0332 0.0317 0.0314 0.0354 0.0345 11.10 1.302 0.0499 0.0496 0.0512 0.0497 0.0491 Tabulated from data in file CL00660.DAT & reduced using program Q02.00D Average Reynolds #: 199000 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.27 -0.306 0.0763 0.0763 0.0749 0.0795 0.0745 -3.75 -0.050 0.0345 0.0333 0.0336 0.0366 0.0347 -2.17 0.174 0.0165 0.0143 0.0174 0.0188 0.0157 -0.62 0.407 0.0120 0.0114 0.0122 0.0122 0.0120 0.91 0.579 0.0100 0.0098 0.0101 0.0096 0.0104 2.49 0.738 0.0102 0.0101 0.0100 0.0103 0.0104 4.00 0.887 0.0111 0.0108 0.0110 0.0113 0.0113 5.53 1.025 0.0129 0.0126 0.0129 0.0130 0.0133 7.07 1.146 0.0169 0.0167 0.0162 0.0172 0.0174 8.60 1.236 0.0234 0.0226 0.0221 0.0240 0.0250 10.11 1.297 0.0322 0.0318 0.0336 0.0323 0.0313 Tabulated from data in file CL00662.DAT & reduced using program Q02.00D Average Reynolds #: 298800 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.30 -0.248 0.0702 0.0701 0.0698 0.0713 0.0696 -3.70 0.040 0.0262 0.0240 0.0239 0.0286 0.0282 -2.28 0.243 0.0128 0.0109 0.0130 0.0135 0.0138 -0.62 0.436 0.0083 0.0069 0.0096 0.0091 0.0078 0.95 0.594 0.0073 0.0069 0.0082 0.0069 0.0071 2.47 0.753 0.0080 0.0075 0.0081 0.0079 0.0083 4.03 0.906 0.0095 0.0093 0.0096 0.0096 0.0094 5.55 1.042 0.0118 0.0116 0.0117 0.0117 0.0120 7.10 1.161 0.0156 0.0153 0.0155 0.0159 0.0160 8.63 1.258 0.0211 0.0202 0.0203 0.0219 0.0219 10.13 1.320 0.0294 0.0289 0.0315 0.0293 0.0277 Tabulated from data in file CL00664.DAT & reduced using program Q02.00D File cr001.drg created on 09-12-1997 at 13:46:23 using program FORMAT