E197 (13.49%) (e197-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E197 (13.49%) (e197-il) Reynolds number: 1,000,000 Max Cl/Cd: 135.9 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e197-il-1000000.txt Download as CSV file: xf-e197-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: E197 (13.49%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.6981 0.07169 0.06961 -0.0546 1.0000 0.0095
-13.500 -0.7231 0.06281 0.06059 -0.0610 1.0000 0.0095
-13.250 -0.7438 0.05549 0.05313 -0.0665 1.0000 0.0095
-13.000 -0.7748 0.04734 0.04478 -0.0724 1.0000 0.0093
-12.750 -0.7832 0.04305 0.04035 -0.0755 1.0000 0.0094
-12.500 -0.7916 0.03934 0.03650 -0.0778 1.0000 0.0095
-12.250 -0.8107 0.03521 0.03217 -0.0788 1.0000 0.0095
-12.000 -0.8182 0.03311 0.02994 -0.0777 1.0000 0.0096
-11.750 -0.8264 0.03166 0.02839 -0.0748 1.0000 0.0096
-11.500 -0.8299 0.03114 0.02779 -0.0708 1.0000 0.0097
-11.250 -0.8374 0.02948 0.02598 -0.0669 1.0000 0.0097
-11.000 -0.8269 0.02659 0.02279 -0.0673 0.9961 0.0100
-10.750 -0.8092 0.02344 0.01938 -0.0687 0.9893 0.0103
-10.500 -0.7793 0.02215 0.01804 -0.0707 0.9847 0.0107
-10.250 -0.7503 0.02105 0.01684 -0.0722 0.9764 0.0110
-10.000 -0.7198 0.02009 0.01578 -0.0738 0.9648 0.0113
-9.750 -0.6907 0.01916 0.01473 -0.0749 0.9448 0.0117
-9.500 -0.6676 0.01842 0.01383 -0.0745 0.9137 0.0120
-9.000 -0.6280 0.01729 0.01230 -0.0721 0.8561 0.0127
-8.750 -0.6061 0.01691 0.01176 -0.0712 0.8341 0.0129
-8.500 -0.5841 0.01642 0.01112 -0.0703 0.8148 0.0131
-8.250 -0.5672 0.01505 0.00956 -0.0688 0.7980 0.0135
-8.000 -0.5477 0.01411 0.00850 -0.0677 0.7831 0.0140
-7.750 -0.5253 0.01354 0.00783 -0.0670 0.7696 0.0144
-7.500 -0.5017 0.01311 0.00731 -0.0664 0.7574 0.0149
-7.000 -0.4526 0.01236 0.00639 -0.0654 0.7359 0.0160
-6.750 -0.4277 0.01199 0.00594 -0.0650 0.7266 0.0165
-6.500 -0.4025 0.01165 0.00550 -0.0646 0.7178 0.0169
-6.250 -0.3766 0.01136 0.00515 -0.0643 0.7100 0.0172
-6.000 -0.3527 0.01080 0.00447 -0.0636 0.7024 0.0180
-5.750 -0.3271 0.01043 0.00403 -0.0633 0.6955 0.0191
-5.500 -0.3008 0.01017 0.00371 -0.0631 0.6887 0.0202
-5.250 -0.2741 0.00994 0.00343 -0.0629 0.6829 0.0215
-5.000 -0.2473 0.00972 0.00315 -0.0627 0.6767 0.0232
-4.750 -0.2209 0.00947 0.00287 -0.0624 0.6711 0.0278
-4.500 -0.1951 0.00904 0.00258 -0.0622 0.6660 0.0558
-4.250 -0.1691 0.00870 0.00237 -0.0620 0.6608 0.0879
-4.000 -0.1427 0.00846 0.00220 -0.0618 0.6558 0.1179
-3.750 -0.1158 0.00818 0.00204 -0.0618 0.6513 0.1527
-3.500 -0.0895 0.00787 0.00189 -0.0617 0.6466 0.1986
-3.250 -0.0629 0.00764 0.00176 -0.0615 0.6420 0.2414
-3.000 -0.0361 0.00739 0.00165 -0.0615 0.6379 0.2864
-2.750 -0.0094 0.00711 0.00156 -0.0614 0.6336 0.3415
-2.500 0.0175 0.00692 0.00150 -0.0613 0.6294 0.3920
-2.250 0.0449 0.00683 0.00147 -0.0613 0.6252 0.4274
-2.000 0.0730 0.00674 0.00144 -0.0613 0.6214 0.4532
-1.750 0.1010 0.00667 0.00141 -0.0614 0.6174 0.4740
-1.500 0.1289 0.00664 0.00138 -0.0614 0.6134 0.4949
-1.250 0.1570 0.00662 0.00137 -0.0614 0.6095 0.5104
-1.000 0.1854 0.00657 0.00136 -0.0615 0.6058 0.5247
-0.750 0.2136 0.00653 0.00134 -0.0616 0.6019 0.5400
-0.500 0.2415 0.00652 0.00134 -0.0616 0.5980 0.5556
-0.250 0.2696 0.00651 0.00135 -0.0617 0.5942 0.5723
0.000 0.2978 0.00646 0.00135 -0.0617 0.5906 0.5901
0.250 0.3258 0.00642 0.00136 -0.0618 0.5867 0.6089
0.500 0.3535 0.00641 0.00138 -0.0617 0.5827 0.6288
1.000 0.4091 0.00632 0.00144 -0.0617 0.5752 0.6774
1.250 0.4364 0.00627 0.00147 -0.0616 0.5711 0.7067
1.500 0.4633 0.00624 0.00151 -0.0614 0.5670 0.7394
1.750 0.4903 0.00617 0.00157 -0.0612 0.5631 0.7747
2.000 0.5168 0.00608 0.00162 -0.0609 0.5589 0.8131
2.250 0.5424 0.00603 0.00168 -0.0603 0.5544 0.8546
2.500 0.5673 0.00598 0.00176 -0.0595 0.5496 0.9004
2.750 0.5955 0.00596 0.00183 -0.0594 0.5441 0.9414
3.000 0.6294 0.00604 0.00190 -0.0606 0.5379 0.9648
3.250 0.6655 0.00609 0.00196 -0.0625 0.5317 0.9774
3.500 0.7022 0.00616 0.00202 -0.0644 0.5249 0.9855
3.750 0.7408 0.00623 0.00209 -0.0669 0.5179 0.9907
4.000 0.7782 0.00631 0.00215 -0.0690 0.5100 0.9954
4.250 0.8171 0.00638 0.00221 -0.0716 0.5020 0.9992
4.500 0.8448 0.00648 0.00229 -0.0717 0.4935 1.0000
4.750 0.8690 0.00656 0.00238 -0.0710 0.4847 1.0000
5.000 0.8925 0.00668 0.00247 -0.0702 0.4753 1.0000
5.250 0.9162 0.00680 0.00258 -0.0694 0.4648 1.0000
5.500 0.9402 0.00693 0.00270 -0.0687 0.4537 1.0000
5.750 0.9635 0.00709 0.00283 -0.0679 0.4394 1.0000
6.000 0.9859 0.00731 0.00299 -0.0669 0.4211 1.0000
6.250 1.0083 0.00755 0.00317 -0.0660 0.3997 1.0000
6.500 1.0284 0.00794 0.00342 -0.0647 0.3661 1.0000
6.750 1.0466 0.00847 0.00375 -0.0631 0.3227 1.0000
7.000 1.0620 0.00919 0.00420 -0.0611 0.2703 1.0000
7.250 1.0785 0.00985 0.00465 -0.0593 0.2289 1.0000
7.500 1.0939 0.01057 0.00515 -0.0574 0.1874 1.0000
7.750 1.1101 0.01121 0.00562 -0.0557 0.1540 1.0000
8.000 1.1259 0.01186 0.00610 -0.0538 0.1250 1.0000
8.250 1.1414 0.01248 0.00659 -0.0520 0.1008 1.0000
8.500 1.1560 0.01311 0.00710 -0.0500 0.0805 1.0000
8.750 1.1713 0.01366 0.00759 -0.0481 0.0657 1.0000
9.000 1.1849 0.01420 0.00807 -0.0459 0.0543 1.0000
9.250 1.1946 0.01477 0.00860 -0.0430 0.0436 1.0000
9.500 1.2032 0.01543 0.00920 -0.0400 0.0336 1.0000
9.750 1.2085 0.01628 0.00997 -0.0367 0.0221 1.0000
10.000 1.2131 0.01723 0.01088 -0.0336 0.0135 1.0000
10.250 1.2212 0.01810 0.01176 -0.0311 0.0107 1.0000
10.500 1.2301 0.01899 0.01270 -0.0289 0.0093 1.0000
10.750 1.2398 0.01989 0.01364 -0.0271 0.0086 1.0000
11.000 1.2487 0.02091 0.01470 -0.0253 0.0081 1.0000
11.250 1.2536 0.02226 0.01612 -0.0232 0.0075 1.0000
11.500 1.2622 0.02344 0.01737 -0.0217 0.0073 1.0000
11.750 1.2716 0.02463 0.01861 -0.0205 0.0070 1.0000
12.000 1.2788 0.02603 0.02009 -0.0191 0.0067 1.0000
12.250 1.2881 0.02732 0.02143 -0.0181 0.0065 1.0000
12.500 1.2946 0.02888 0.02306 -0.0170 0.0064 1.0000
12.750 1.3002 0.03057 0.02481 -0.0160 0.0062 1.0000
13.000 1.3038 0.03247 0.02677 -0.0150 0.0058 1.0000
13.250 1.3090 0.03428 0.02866 -0.0142 0.0058 1.0000
13.500 1.3050 0.03700 0.03147 -0.0132 0.0055 1.0000
13.750 1.3097 0.03895 0.03349 -0.0126 0.0056 1.0000
14.000 1.3009 0.04230 0.03696 -0.0118 0.0054 1.0000
14.250 1.2973 0.04525 0.04001 -0.0113 0.0053 1.0000
14.500 1.2975 0.04790 0.04274 -0.0110 0.0053 1.0000
14.750 1.3034 0.05001 0.04492 -0.0109 0.0052 1.0000
15.000 1.3030 0.05287 0.04788 -0.0109 0.0052 1.0000
15.250 1.3032 0.05574 0.05084 -0.0110 0.0051 1.0000
15.500 1.3048 0.05854 0.05371 -0.0112 0.0051 1.0000
15.750 1.3049 0.06160 0.05686 -0.0115 0.0050 1.0000
16.000 1.3017 0.06511 0.06047 -0.0120 0.0050 1.0000
16.250 1.3026 0.06823 0.06368 -0.0126 0.0049 1.0000
16.500 1.2980 0.07213 0.06768 -0.0134 0.0049 1.0000
16.750 1.2984 0.07548 0.07110 -0.0143 0.0048 1.0000
17.000 1.2949 0.07944 0.07516 -0.0153 0.0047 1.0000
17.250 1.2905 0.08360 0.07942 -0.0165 0.0047 1.0000
17.500 1.2861 0.08788 0.08380 -0.0179 0.0047 1.0000
17.750 1.2833 0.09202 0.08804 -0.0194 0.0047 1.0000
18.000 1.2788 0.09650 0.09261 -0.0211 0.0046 1.0000
18.250 1.2720 0.10141 0.09763 -0.0230 0.0046 1.0000
18.500 1.2667 0.10624 0.10257 -0.0250 0.0046 1.0000
18.750 1.2606 0.11130 0.10774 -0.0273 0.0045 1.0000
19.000 1.2535 0.11656 0.11312 -0.0297 0.0045 1.0000
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Polar data table (+)
Polar graphs
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