XFOIL Version 6.96 Calculated polar for: NLR-7301 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -1.3153 0.07902 0.07458 -0.0489 1.0000 0.0243 -19.500 -1.3242 0.07441 0.06988 -0.0509 1.0000 0.0244 -19.250 -1.3304 0.07023 0.06561 -0.0527 1.0000 0.0246 -19.000 -1.3344 0.06644 0.06175 -0.0542 1.0000 0.0248 -18.750 -1.3360 0.06306 0.05830 -0.0554 1.0000 0.0249 -18.500 -1.3355 0.06000 0.05517 -0.0564 1.0000 0.0251 -18.250 -1.3340 0.05709 0.05221 -0.0573 1.0000 0.0253 -18.000 -1.3314 0.05438 0.04943 -0.0581 1.0000 0.0254 -17.750 -1.3268 0.05197 0.04697 -0.0587 1.0000 0.0256 -17.500 -1.3221 0.04958 0.04452 -0.0593 1.0000 0.0258 -17.250 -1.3153 0.04748 0.04237 -0.0597 1.0000 0.0260 -17.000 -1.3086 0.04539 0.04022 -0.0601 1.0000 0.0262 -16.750 -1.3001 0.04354 0.03832 -0.0604 1.0000 0.0264 -16.500 -1.2917 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0.0644 0.6185 3.250 0.6335 0.01140 0.00416 -0.0708 0.0612 0.6206 3.500 0.6612 0.01159 0.00431 -0.0706 0.0580 0.6225 3.750 0.6889 0.01178 0.00447 -0.0705 0.0551 0.6243 4.000 0.7164 0.01198 0.00464 -0.0703 0.0527 0.6270 4.250 0.7439 0.01217 0.00483 -0.0701 0.0506 0.6296 4.500 0.7710 0.01239 0.00503 -0.0699 0.0489 0.6323 4.750 0.7982 0.01260 0.00523 -0.0696 0.0477 0.6351 5.000 0.8252 0.01282 0.00544 -0.0694 0.0466 0.6380 5.250 0.8520 0.01305 0.00566 -0.0691 0.0457 0.6407 5.500 0.8785 0.01330 0.00588 -0.0688 0.0449 0.6430 5.750 0.9047 0.01357 0.00613 -0.0684 0.0441 0.6449 6.000 0.9309 0.01381 0.00638 -0.0680 0.0436 0.6476 6.250 0.9571 0.01405 0.00663 -0.0676 0.0431 0.6505 6.500 0.9830 0.01431 0.00690 -0.0672 0.0427 0.6533 6.750 1.0086 0.01457 0.00718 -0.0668 0.0423 0.6561 7.000 1.0339 0.01485 0.00746 -0.0662 0.0419 0.6589 7.250 1.0588 0.01515 0.00776 -0.0657 0.0415 0.6615 7.500 1.0834 0.01545 0.00806 -0.0651 0.0411 0.6640 7.750 1.1077 0.01578 0.00838 -0.0644 0.0407 0.6662 8.000 1.1315 0.01611 0.00872 -0.0637 0.0403 0.6689 8.250 1.1547 0.01648 0.00910 -0.0629 0.0399 0.6722 8.500 1.1769 0.01687 0.00951 -0.0620 0.0396 0.6753 8.750 1.1978 0.01722 0.00989 -0.0608 0.0394 0.6781 9.000 1.2186 0.01757 0.01026 -0.0596 0.0392 0.6809 9.250 1.2399 0.01795 0.01067 -0.0585 0.0391 0.6836 9.500 1.2611 0.01835 0.01109 -0.0575 0.0389 0.6861 9.750 1.2818 0.01878 0.01154 -0.0564 0.0388 0.6883 10.000 1.3022 0.01923 0.01201 -0.0553 0.0386 0.6903 10.250 1.3222 0.01969 0.01251 -0.0542 0.0384 0.6934 10.500 1.3418 0.02018 0.01304 -0.0530 0.0383 0.6963 10.750 1.3609 0.02069 0.01359 -0.0518 0.0381 0.6992 11.000 1.3796 0.02123 0.01417 -0.0506 0.0379 0.7021 11.250 1.3979 0.02180 0.01477 -0.0494 0.0378 0.7050 11.500 1.4157 0.02240 0.01540 -0.0482 0.0376 0.7079 11.750 1.4332 0.02303 0.01606 -0.0470 0.0375 0.7105 12.000 1.4501 0.02370 0.01676 -0.0457 0.0373 0.7125 12.250 1.4667 0.02439 0.01750 -0.0444 0.0372 0.7158 12.500 1.4828 0.02511 0.01828 -0.0432 0.0370 0.7187 12.750 1.4983 0.02589 0.01910 -0.0419 0.0369 0.7216 13.000 1.5134 0.02670 0.01996 -0.0406 0.0368 0.7245 13.250 1.5276 0.02758 0.02088 -0.0393 0.0366 0.7273 13.500 1.5415 0.02851 0.02185 -0.0380 0.0365 0.7300 13.750 1.5545 0.02949 0.02288 -0.0367 0.0364 0.7324 14.000 1.5667 0.03055 0.02398 -0.0354 0.0363 0.7344 14.250 1.5785 0.03166 0.02514 -0.0341 0.0362 0.7374 14.500 1.5890 0.03287 0.02642 -0.0328 0.0361 0.7408 14.750 1.5991 0.03414 0.02775 -0.0316 0.0360 0.7441 15.000 1.6074 0.03557 0.02925 -0.0303 0.0358 0.7474 15.250 1.6150 0.03709 0.03083 -0.0290 0.0357 0.7504 15.500 1.6212 0.03876 0.03256 -0.0278 0.0356 0.7531 15.750 1.6262 0.04056 0.03443 -0.0266 0.0355 0.7554 16.000 1.6304 0.04248 0.03643 -0.0256 0.0354 0.7582 16.250 1.6365 0.04430 0.03833 -0.0247 0.0353 0.7617 16.500 1.6430 0.04612 0.04024 -0.0240 0.0353 0.7652 16.750 1.6484 0.04812 0.04232 -0.0234 0.0352 0.7687 17.000 1.6529 0.05027 0.04455 -0.0229 0.0352 0.7721 17.250 1.6572 0.05251 0.04688 -0.0225 0.0351 0.7752 17.500 1.6597 0.05504 0.04949 -0.0223 0.0351 0.7781 17.750 1.6609 0.05776 0.05232 -0.0223 0.0350 0.7815 18.000 1.6607 0.06075 0.05540 -0.0224 0.0350 0.7848 18.250 1.6598 0.06393 0.05869 -0.0228 0.0349 0.7881 18.500 1.6575 0.06740 0.06226 -0.0234 0.0349 0.7915 18.750 1.6536 0.07116 0.06612 -0.0242 0.0348 0.7946 19.000 1.6480 0.07527 0.07035 -0.0253 0.0348 0.7976 19.250 1.6409 0.07970 0.07490 -0.0268 0.0347 0.8011