XFOIL Version 6.96 Calculated polar for: BOEING 707 .40 SPAN AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.3786 0.09015 0.08848 -0.0279 1.0000 0.0093 -10.000 -0.3800 0.08605 0.08439 -0.0289 1.0000 0.0093 -9.750 -0.3811 0.08213 0.08048 -0.0299 1.0000 0.0093 -9.500 -0.3842 0.07785 0.07622 -0.0311 1.0000 0.0093 -9.250 -0.3870 0.07333 0.07170 -0.0328 0.9983 0.0093 -9.000 -0.3880 0.06821 0.06658 -0.0360 0.9875 0.0093 -8.750 -0.3847 0.06140 0.05977 -0.0434 0.9741 0.0093 -8.500 -0.3879 0.05344 0.05172 -0.0547 0.9547 0.0093 -8.250 -0.3916 0.04878 0.04686 -0.0581 0.9115 0.0093 -8.000 -0.4002 0.04564 0.04345 -0.0568 0.8516 0.0093 -7.750 -0.4061 0.04243 0.03996 -0.0552 0.7922 0.0093 -7.500 -0.4088 0.03948 0.03662 -0.0534 0.7029 0.0093 -7.250 -0.4066 0.03582 0.03274 -0.0524 0.6718 0.0093 -7.000 -0.4012 0.03232 0.02908 -0.0515 0.6562 0.0092 -6.750 -0.3958 0.02876 0.02537 -0.0506 0.6430 0.0090 -6.500 -0.3857 0.02543 0.02187 -0.0495 0.6331 0.0088 -6.250 -0.3739 0.02197 0.01820 -0.0482 0.6233 0.0089 -5.750 -0.3447 0.01629 0.01208 -0.0457 0.6026 0.0099 -5.250 -0.3052 0.02972 0.02489 -0.0472 0.5841 0.0125 -5.000 -0.2849 0.02768 0.02263 -0.0460 0.5735 0.0125 -4.750 -0.2692 0.02414 0.01878 -0.0442 0.5634 0.0128 -4.500 -0.2483 0.02276 0.01723 -0.0434 0.5473 0.0131 -4.250 -0.2266 0.02146 0.01567 -0.0423 0.5096 0.0132 -4.000 -0.2119 0.02171 0.01502 -0.0404 0.2486 0.0135 -3.500 -0.1647 0.01844 0.01125 -0.0381 0.2107 0.0114 -2.000 -0.0182 0.01216 0.00383 -0.0328 0.0303 0.0093 -1.750 0.0064 0.01180 0.00340 -0.0321 0.0278 0.0093 -1.500 0.0304 0.01138 0.00290 -0.0314 0.0260 0.0094 -1.250 0.0549 0.01103 0.00249 -0.0307 0.0246 0.0097 -1.000 0.0804 0.01084 0.00224 -0.0302 0.0232 0.0100 -0.750 0.1064 0.01072 0.00208 -0.0298 0.0221 0.0103 -0.500 0.1325 0.01064 0.00196 -0.0295 0.0214 0.0109 -0.250 0.1588 0.01058 0.00189 -0.0292 0.0211 0.0115 0.000 0.1853 0.01056 0.00184 -0.0289 0.0207 0.0119 0.250 0.2118 0.01055 0.00181 -0.0287 0.0193 0.0124 0.750 0.2644 0.01061 0.00184 -0.0281 0.0108 0.0153 1.000 0.2908 0.01064 0.00190 -0.0278 0.0105 0.0209 1.250 0.3172 0.01069 0.00197 -0.0276 0.0103 0.0254 1.500 0.3436 0.01077 0.00205 -0.0273 0.0101 0.0291 1.750 0.3698 0.01085 0.00214 -0.0270 0.0099 0.0314 2.000 0.3959 0.01095 0.00225 -0.0267 0.0099 0.0356 2.250 0.4219 0.01105 0.00238 -0.0264 0.0098 0.0421 2.500 0.4474 0.01110 0.00254 -0.0260 0.0097 0.1054 2.750 0.4725 0.01112 0.00268 -0.0256 0.0097 0.1756 3.000 0.4946 0.01075 0.00283 -0.0248 0.0097 0.4033 3.250 0.5199 0.01086 0.00299 -0.0244 0.0096 0.4221 3.500 0.5448 0.01092 0.00316 -0.0239 0.0096 0.4532 3.750 0.5638 0.01044 0.00335 -0.0224 0.0096 0.6854 4.000 0.5883 0.01056 0.00355 -0.0219 0.0097 0.7120 4.250 0.6128 0.01076 0.00380 -0.0213 0.0095 0.7278 4.500 0.6366 0.01097 0.00407 -0.0206 0.0094 0.7490 4.750 0.6588 0.01133 0.00449 -0.0196 0.0092 0.7701 5.000 0.6814 0.01161 0.00483 -0.0187 0.0091 0.7916 5.250 0.7034 0.01189 0.00518 -0.0177 0.0091 0.8165 5.500 0.7227 0.01236 0.00573 -0.0162 0.0090 0.8446 5.750 0.7433 0.01266 0.00614 -0.0149 0.0089 0.8774 6.250 0.8206 0.01338 0.00710 -0.0204 0.0088 0.9776 6.500 0.8590 0.01395 0.00766 -0.0233 0.0087 1.0000 6.750 0.8801 0.01430 0.00805 -0.0222 0.0085 1.0000 7.000 0.8995 0.01480 0.00856 -0.0208 0.0085 1.0000 7.250 0.9193 0.01529 0.00906 -0.0195 0.0084 1.0000 7.500 0.9388 0.01581 0.00961 -0.0182 0.0082 1.0000 7.750 0.9581 0.01636 0.01018 -0.0169 0.0082 1.0000 8.000 0.9771 0.01698 0.01082 -0.0155 0.0081 1.0000 8.250 0.9956 0.01766 0.01152 -0.0142 0.0079 1.0000 8.500 1.0142 0.01836 0.01224 -0.0128 0.0078 1.0000 8.750 1.0330 0.01905 0.01296 -0.0116 0.0078 1.0000 9.000 1.0514 0.01983 0.01377 -0.0103 0.0078 1.0000 9.250 1.0699 0.02073 0.01468 -0.0091 0.0077 1.0000 9.500 1.0884 0.02155 0.01553 -0.0079 0.0077 1.0000 9.750 1.1099 0.02290 0.01680 -0.0075 0.0075 1.0000 10.000 1.1254 0.02344 0.01750 -0.0057 0.0076 1.0000 10.250 1.1485 0.02486 0.01884 -0.0056 0.0075 1.0000 10.500 1.1637 0.02568 0.01977 -0.0040 0.0075 1.0000 10.750 1.1798 0.02669 0.02087 -0.0027 0.0075 1.0000 11.000 1.1956 0.02777 0.02203 -0.0013 0.0075 1.0000 11.250 1.2209 0.02944 0.02365 -0.0018 0.0075 1.0000 11.500 1.2390 0.03167 0.02596 -0.0013 0.0072 1.0000 11.750 1.2442 0.03258 0.02704 0.0016 0.0072 1.0000 12.000 1.2428 0.03343 0.02808 0.0055 0.0071 1.0000 12.250 1.2464 0.03452 0.02928 0.0085 0.0071 1.0000 12.500 1.2423 0.03580 0.03074 0.0122 0.0071 1.0000 12.750 1.2423 0.03716 0.03222 0.0148 0.0071 1.0000 13.000 1.2399 0.03879 0.03400 0.0173 0.0071 1.0000 13.250 1.2343 0.04063 0.03600 0.0196 0.0071 1.0000 13.500 1.2264 0.04281 0.03835 0.0214 0.0071 1.0000 13.750 1.2180 0.04529 0.04101 0.0225 0.0071 1.0000 14.000 1.2114 0.04796 0.04382 0.0230 0.0070 1.0000 14.250 1.2079 0.05094 0.04692 0.0232 0.0071 1.0000 14.500 1.1948 0.05463 0.05080 0.0225 0.0071 1.0000 14.750 1.1783 0.05913 0.05550 0.0209 0.0070 1.0000 15.000 1.1677 0.06333 0.05985 0.0193 0.0070 1.0000 15.250 1.1578 0.06783 0.06445 0.0178 0.0070 1.0000 15.500 1.1429 0.07320 0.06997 0.0153 0.0071 1.0000 15.750 1.1239 0.07970 0.07665 0.0114 0.0070 1.0000 16.000 1.1115 0.08546 0.08250 0.0086 0.0071 1.0000 16.250 1.0955 0.09225 0.08942 0.0047 0.0071 1.0000 16.500 1.0734 0.10117 0.09852 -0.0013 0.0070 1.0000 16.750 1.0581 0.10894 0.10639 -0.0061 0.0071 1.0000 17.000 1.0514 0.11418 0.11166 -0.0082 0.0071 1.0000 17.250 1.0331 0.12335 0.12095 -0.0140 0.0072 1.0000 17.500 1.0191 0.13151 0.12920 -0.0188 0.0072 1.0000 17.750 0.9956 0.14309 0.14089 -0.0262 0.0072 1.0000 18.000 0.9848 0.15060 0.14846 -0.0304 0.0072 1.0000