EPPLER 584 AIRFOIL (e584-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
Details | Polar file |
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Airfoil: EPPLER 584 AIRFOIL (e584-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.78 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e584-il-1000000-n5.txt Download as CSV file: xf-e584-il-1000000-n5.csv |
XFOIL Version 6.96 Calculated polar for: EPPLER 584 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 ------ -------- --------- --------- -------- -------- -------- -11.250 -0.3334 0.03772 0.03386 -0.1394 0.6522 0.0040 -11.000 -0.3753 0.03288 0.02872 -0.1352 0.6514 0.0040 -10.750 -0.3853 0.03082 0.02651 -0.1320 0.6506 0.0040 -10.500 -0.3976 0.02861 0.02411 -0.1279 0.6498 0.0040 -10.250 -0.4048 0.02691 0.02224 -0.1237 0.6490 0.0039 -10.000 -0.4165 0.02490 0.01997 -0.1184 0.6482 0.0039 -9.750 -0.4101 0.02360 0.01850 -0.1157 0.6474 0.0039 -9.500 -0.4014 0.02226 0.01698 -0.1133 0.6466 0.0039 -9.250 -0.3897 0.02105 0.01558 -0.1112 0.6457 0.0039 -9.000 -0.3765 0.01981 0.01416 -0.1092 0.6448 0.0039 -8.750 -0.3600 0.01886 0.01305 -0.1077 0.6440 0.0039 -8.500 -0.3421 0.01797 0.01201 -0.1064 0.6431 0.0039 -8.250 -0.3230 0.01717 0.01107 -0.1052 0.6421 0.0039 -8.000 -0.3026 0.01649 0.01028 -0.1042 0.6411 0.0039 -7.750 -0.2818 0.01582 0.00949 -0.1032 0.6399 0.0040 -7.500 -0.2601 0.01524 0.00881 -0.1024 0.6386 0.0040 -7.250 -0.2376 0.01472 0.00823 -0.1017 0.6377 0.0040 -7.000 -0.2149 0.01420 0.00763 -0.1009 0.6370 0.0040 -6.750 -0.1918 0.01373 0.00711 -0.1003 0.6362 0.0040 -6.500 -0.1682 0.01332 0.00665 -0.0997 0.6353 0.0040 -6.250 -0.1446 0.01291 0.00620 -0.0991 0.6343 0.0041 -6.000 -0.1205 0.01255 0.00580 -0.0986 0.6333 0.0041 -5.750 -0.0969 0.01215 0.00535 -0.0980 0.6321 0.0041 -5.500 -0.0728 0.01178 0.00495 -0.0975 0.6308 0.0042 -5.250 -0.0486 0.01144 0.00457 -0.0970 0.6295 0.0044 -5.000 -0.0235 0.01120 0.00429 -0.0966 0.6284 0.0045 -4.750 0.0018 0.01097 0.00404 -0.0963 0.6271 0.0048 -4.500 0.0274 0.01079 0.00382 -0.0960 0.6257 0.0050 -4.250 0.0533 0.01064 0.00364 -0.0958 0.6242 0.0055 -4.000 0.0794 0.01045 0.00345 -0.0956 0.6231 0.0059 -3.750 0.1055 0.01026 0.00326 -0.0954 0.6218 0.0068 -3.500 0.1318 0.01009 0.00310 -0.0953 0.6202 0.0085 -3.250 0.1581 0.00992 0.00295 -0.0952 0.6186 0.0122 -3.000 0.1842 0.00974 0.00281 -0.0950 0.6169 0.0212 -2.750 0.2105 0.00957 0.00269 -0.0949 0.6152 0.0326 -2.500 0.2367 0.00940 0.00258 -0.0948 0.6135 0.0487 -2.250 0.2620 0.00915 0.00248 -0.0946 0.6118 0.0869 -2.000 0.2863 0.00882 0.00238 -0.0943 0.6101 0.1557 -1.750 0.3113 0.00846 0.00229 -0.0941 0.6084 0.2346 -1.500 0.3368 0.00814 0.00220 -0.0941 0.6064 0.3110 -1.250 0.3620 0.00773 0.00211 -0.0940 0.6041 0.4118 -1.000 0.3860 0.00705 0.00196 -0.0940 0.6017 0.5803 -0.750 0.4101 0.00653 0.00203 -0.0936 0.5993 0.7574 -0.500 0.4380 0.00660 0.00210 -0.0936 0.5971 0.7838 -0.250 0.4665 0.00666 0.00214 -0.0938 0.5947 0.7951 0.000 0.4957 0.00673 0.00219 -0.0942 0.5919 0.8065 0.250 0.5227 0.00688 0.00236 -0.0940 0.5888 0.8178 0.500 0.5491 0.00705 0.00253 -0.0936 0.5856 0.8277 0.750 0.5756 0.00717 0.00264 -0.0933 0.5824 0.8328 1.000 0.6040 0.00719 0.00264 -0.0937 0.5792 0.8339 1.250 0.6325 0.00721 0.00263 -0.0940 0.5756 0.8347 1.500 0.6605 0.00724 0.00263 -0.0943 0.5717 0.8355 1.750 0.6879 0.00728 0.00263 -0.0944 0.5678 0.8363 2.000 0.7159 0.00731 0.00264 -0.0947 0.5642 0.8368 2.250 0.7439 0.00735 0.00267 -0.0950 0.5602 0.8373 2.500 0.7713 0.00740 0.00269 -0.0952 0.5558 0.8378 3.000 0.8258 0.00753 0.00277 -0.0955 0.5469 0.8390 3.250 0.8528 0.00759 0.00282 -0.0956 0.5415 0.8394 3.500 0.8784 0.00768 0.00288 -0.0954 0.5360 0.8399 3.750 0.9056 0.00772 0.00293 -0.0956 0.5311 0.8405 4.000 0.9318 0.00779 0.00299 -0.0955 0.5250 0.8410 4.500 0.9830 0.00796 0.00315 -0.0953 0.5119 0.8420 4.750 1.0069 0.00808 0.00324 -0.0948 0.5038 0.8425 5.000 1.0317 0.00819 0.00334 -0.0945 0.4950 0.8430 5.250 1.0547 0.00833 0.00346 -0.0938 0.4860 0.8436 5.500 1.0768 0.00850 0.00360 -0.0930 0.4751 0.8442 5.750 1.0979 0.00866 0.00374 -0.0920 0.4646 0.8450 6.000 1.1164 0.00885 0.00391 -0.0904 0.4533 0.8458 6.500 1.1532 0.00929 0.00429 -0.0874 0.4306 0.8472 6.750 1.1711 0.00955 0.00452 -0.0858 0.4191 0.8480 7.000 1.1875 0.00985 0.00478 -0.0840 0.4068 0.8487 7.250 1.2030 0.01018 0.00508 -0.0821 0.3938 0.8495 7.500 1.2172 0.01056 0.00541 -0.0799 0.3788 0.8504 7.750 1.2294 0.01099 0.00578 -0.0775 0.3625 0.8512 8.000 1.2430 0.01140 0.00616 -0.0753 0.3488 0.8520 8.250 1.2539 0.01190 0.00661 -0.0728 0.3333 0.8529 8.500 1.2641 0.01244 0.00711 -0.0702 0.3185 0.8537 8.750 1.2734 0.01304 0.00766 -0.0676 0.3041 0.8545 9.000 1.2814 0.01372 0.00830 -0.0649 0.2895 0.8552 9.250 1.2882 0.01450 0.00902 -0.0622 0.2747 0.8559 9.500 1.2931 0.01538 0.00987 -0.0593 0.2592 0.8572 9.750 1.2987 0.01630 0.01076 -0.0567 0.2455 0.8585 10.000 1.3038 0.01731 0.01174 -0.0541 0.2325 0.8596 10.250 1.3076 0.01846 0.01286 -0.0516 0.2183 0.8607 10.500 1.3128 0.01962 0.01399 -0.0494 0.2067 0.8617 10.750 1.3179 0.02083 0.01518 -0.0473 0.1945 0.8627 11.000 1.3224 0.02214 0.01646 -0.0452 0.1820 0.8637 11.250 1.3239 0.02368 0.01796 -0.0430 0.1674 0.8648 11.500 1.3250 0.02532 0.01954 -0.0409 0.1528 0.8658 11.750 1.3276 0.02693 0.02111 -0.0391 0.1399 0.8668 12.000 1.3319 0.02848 0.02264 -0.0376 0.1293 0.8678 12.250 1.3358 0.03012 0.02425 -0.0361 0.1191 0.8687 12.500 1.3390 0.03187 0.02598 -0.0347 0.1088 0.8696 12.750 1.3447 0.03350 0.02760 -0.0337 0.1003 0.8704 13.000 1.3504 0.03516 0.02925 -0.0326 0.0926 0.8712 13.500 1.3538 0.03919 0.03322 -0.0303 0.0721 0.8731 13.750 1.3573 0.04111 0.03513 -0.0293 0.0646 0.8741 14.000 1.3614 0.04302 0.03705 -0.0285 0.0577 0.8752 14.250 1.3579 0.04566 0.03961 -0.0274 0.0447 0.8762 14.500 1.3601 0.04789 0.04183 -0.0267 0.0384 0.8772 14.750 1.3676 0.04966 0.04364 -0.0262 0.0358 0.8783 15.000 1.3655 0.05239 0.04635 -0.0256 0.0278 0.8793 15.250 1.3722 0.05433 0.04834 -0.0253 0.0256 0.8805 15.500 1.3753 0.05671 0.05073 -0.0250 0.0219 0.8817 16.000 1.3822 0.06152 0.05561 -0.0248 0.0164 0.8841 16.250 1.3862 0.06394 0.05806 -0.0248 0.0143 0.8852 16.500 1.3899 0.06646 0.06063 -0.0249 0.0127 0.8863 16.750 1.3927 0.06914 0.06335 -0.0251 0.0110 0.8872 17.000 1.3968 0.07167 0.06594 -0.0253 0.0100 0.8885 17.250 1.3999 0.07435 0.06869 -0.0256 0.0091 0.8898 17.500 1.4031 0.07706 0.07147 -0.0260 0.0084 0.8911 17.750 1.4043 0.08009 0.07456 -0.0265 0.0072 0.8925 18.000 1.4069 0.08297 0.07751 -0.0270 0.0066 0.8939 18.250 1.4082 0.08609 0.08071 -0.0277 0.0058 0.8953 18.500 1.4102 0.08914 0.08382 -0.0284 0.0054 0.8968 18.750 1.4098 0.09256 0.08732 -0.0293 0.0046 0.8983 19.000 1.4096 0.09602 0.09085 -0.0303 0.0040 0.8997 |
Polar data table (+)
Polar graphs
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