XFOIL Version 6.96 Calculated polar for: P-51D TIP (BL215) AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.5127 0.09605 0.09161 -0.0349 1.0000 0.0238 -10.250 -0.5148 0.09054 0.08614 -0.0389 0.9596 0.0237 -10.000 -0.5153 0.08292 0.07849 -0.0465 0.9356 0.0236 -9.750 -0.5212 0.07599 0.07147 -0.0529 0.9198 0.0233 -9.500 -0.5332 0.07028 0.06563 -0.0570 0.9071 0.0232 -9.250 -0.5461 0.06588 0.06110 -0.0587 0.8967 0.0230 -8.750 -0.5711 0.05815 0.05294 -0.0580 0.8806 0.0232 -8.500 -0.5773 0.05412 0.04859 -0.0571 0.8748 0.0234 -8.250 -0.5790 0.05000 0.04410 -0.0560 0.8696 0.0236 -8.000 -0.5764 0.04598 0.03965 -0.0548 0.8650 0.0238 -7.750 -0.5704 0.04202 0.03514 -0.0532 0.8612 0.0243 -7.500 -0.5598 0.03834 0.03080 -0.0517 0.8576 0.0249 -7.250 -0.5447 0.03533 0.02744 -0.0509 0.8539 0.0260 -7.000 -0.5253 0.03402 0.02600 -0.0506 0.8505 0.0286 -6.750 -0.5055 0.03192 0.02333 -0.0496 0.8475 0.0321 -6.500 -0.4835 0.02956 0.02056 -0.0489 0.8448 0.0342 -6.250 -0.4595 0.02811 0.01896 -0.0488 0.8417 0.0370 -6.000 -0.4350 0.02708 0.01758 -0.0484 0.8389 0.0424 -5.750 -0.4097 0.02536 0.01580 -0.0483 0.8366 0.0449 -5.500 -0.3838 0.02414 0.01444 -0.0480 0.8345 0.0477 -5.250 -0.3586 0.02313 0.01320 -0.0475 0.8326 0.0508 -5.000 -0.3336 0.02236 0.01227 -0.0472 0.8301 0.0534 -4.750 -0.3109 0.02157 0.01156 -0.0469 0.8274 0.0587 -4.500 -0.2873 0.02105 0.01094 -0.0465 0.8247 0.0638 -4.250 -0.2643 0.02050 0.01027 -0.0458 0.8224 0.0660 -4.000 -0.2418 0.01993 0.00966 -0.0451 0.8204 0.0698 -3.750 -0.2182 0.01953 0.00916 -0.0445 0.8187 0.0763 -3.500 -0.1951 0.01907 0.00870 -0.0441 0.8166 0.0918 -3.250 -0.1773 0.01809 0.00834 -0.0432 0.8142 0.2019 -3.000 -0.1752 0.01669 0.00900 -0.0383 0.8115 0.6154 -2.750 -0.1535 0.01713 0.00929 -0.0368 0.8093 0.7059 -2.500 -0.1348 0.01805 0.01024 -0.0331 0.8074 0.7562 -2.250 -0.1193 0.01910 0.01131 -0.0276 0.8058 0.8020 -2.000 -0.0974 0.01954 0.01169 -0.0248 0.8045 0.8232 -1.750 -0.0741 0.01961 0.01165 -0.0244 0.8023 0.8301 -1.500 -0.0497 0.01963 0.01156 -0.0244 0.8003 0.8338 -1.250 -0.0242 0.01965 0.01147 -0.0245 0.7984 0.8362 -1.000 0.0012 0.01966 0.01139 -0.0247 0.7966 0.8382 -0.750 0.0267 0.01967 0.01132 -0.0249 0.7948 0.8402 -0.500 0.0526 0.01967 0.01124 -0.0251 0.7932 0.8420 -0.250 0.0787 0.01970 0.01120 -0.0254 0.7918 0.8437 0.000 0.1046 0.01976 0.01121 -0.0258 0.7905 0.8456 0.250 0.1282 0.01995 0.01141 -0.0259 0.7883 0.8475 0.500 0.1521 0.02014 0.01161 -0.0260 0.7863 0.8494 0.750 0.1764 0.02032 0.01180 -0.0261 0.7843 0.8512 1.000 0.2014 0.02048 0.01198 -0.0263 0.7824 0.8531 1.250 0.2268 0.02065 0.01217 -0.0265 0.7807 0.8551 1.500 0.2524 0.02085 0.01240 -0.0268 0.7795 0.8573 1.750 0.2783 0.02106 0.01265 -0.0272 0.7783 0.8598 2.000 0.3047 0.02127 0.01293 -0.0274 0.7773 0.8618 2.250 0.3243 0.02171 0.01348 -0.0271 0.7743 0.8646 2.500 0.3449 0.02213 0.01400 -0.0268 0.7716 0.8674 2.750 0.3676 0.02247 0.01444 -0.0267 0.7691 0.8702 3.000 0.3942 0.02265 0.01472 -0.0269 0.7663 0.8728 3.250 0.4244 0.02268 0.01489 -0.0273 0.7638 0.8749 3.500 0.4412 0.02308 0.01544 -0.0263 0.7571 0.8786 3.750 0.4783 0.02244 0.01494 -0.0265 0.7500 0.8806 4.000 0.5105 0.02148 0.01411 -0.0255 0.7358 0.8833 4.250 0.5369 0.02057 0.01340 -0.0239 0.7174 0.8867 4.500 0.5666 0.01878 0.01172 -0.0215 0.6873 0.8893 4.750 0.5882 0.01764 0.01074 -0.0191 0.6450 0.8933 5.000 0.6040 0.01761 0.01091 -0.0173 0.5936 0.8991 5.250 0.6169 0.01740 0.00907 -0.0121 0.3133 0.9034 5.500 0.6215 0.01878 0.00987 -0.0093 0.1981 0.9110 5.750 0.6345 0.01988 0.01054 -0.0076 0.1175 0.9189 6.000 0.6530 0.02085 0.01141 -0.0066 0.0838 0.9280 6.250 0.6762 0.02172 0.01228 -0.0064 0.0673 0.9383 6.500 0.7014 0.02272 0.01334 -0.0068 0.0572 0.9525 6.750 0.7261 0.02392 0.01456 -0.0074 0.0479 1.0000 7.000 0.7452 0.02492 0.01558 -0.0068 0.0399 1.0000 7.250 0.7652 0.02636 0.01710 -0.0061 0.0353 1.0000 7.500 0.7866 0.02776 0.01847 -0.0058 0.0301 1.0000 7.750 0.8119 0.02924 0.02011 -0.0057 0.0264 1.0000 8.000 0.8382 0.03125 0.02214 -0.0059 0.0242 1.0000 8.250 0.8679 0.03388 0.02506 -0.0062 0.0228 1.0000 8.500 0.8922 0.03653 0.02819 -0.0057 0.0209 1.0000 8.750 0.9106 0.03907 0.03115 -0.0048 0.0190 1.0000 9.000 0.9247 0.04181 0.03426 -0.0036 0.0178 1.0000 9.250 0.9343 0.04501 0.03801 -0.0020 0.0173 1.0000 9.500 0.9388 0.04832 0.04170 -0.0001 0.0170 1.0000 9.750 0.9382 0.05171 0.04544 0.0021 0.0168 1.0000 10.000 0.9312 0.05502 0.04906 0.0047 0.0167 1.0000 10.250 0.9197 0.05849 0.05280 0.0072 0.0167 1.0000 10.500 0.9051 0.06222 0.05678 0.0090 0.0167 1.0000 10.750 0.8879 0.06644 0.06124 0.0101 0.0169 1.0000 11.000 0.8686 0.07110 0.06610 0.0103 0.0169 1.0000 11.250 0.8472 0.07647 0.07165 0.0094 0.0172 1.0000 11.500 0.8237 0.08279 0.07813 0.0072 0.0174 1.0000 11.750 0.7997 0.09041 0.08587 0.0033 0.0177 1.0000