E197 (13.49%) (e197-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E197 (13.49%) (e197-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.93 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e197-il-1000000-n5.txt Download as CSV file: xf-e197-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.7823 0.09310 0.09095 -0.0423 1.0000 0.0068
-15.750 -0.8529 0.07636 0.07396 -0.0519 1.0000 0.0066
-15.500 -0.8865 0.06676 0.06421 -0.0576 1.0000 0.0065
-15.250 -0.9168 0.05810 0.05538 -0.0631 1.0000 0.0065
-15.000 -0.9239 0.05333 0.05054 -0.0662 1.0000 0.0066
-14.750 -0.9358 0.04805 0.04514 -0.0697 1.0000 0.0067
-14.500 -0.9564 0.04181 0.03871 -0.0738 1.0000 0.0066
-14.250 -0.9578 0.03843 0.03524 -0.0759 1.0000 0.0068
-14.000 -0.9541 0.03592 0.03265 -0.0773 1.0000 0.0069
-13.750 -0.9570 0.03293 0.02954 -0.0787 1.0000 0.0070
-13.500 -0.9658 0.02991 0.02637 -0.0791 1.0000 0.0070
-13.250 -0.9629 0.02840 0.02478 -0.0783 1.0000 0.0071
-13.000 -0.9654 0.02687 0.02314 -0.0763 1.0000 0.0072
-12.750 -0.9640 0.02597 0.02217 -0.0736 1.0000 0.0073
-12.500 -0.9649 0.02491 0.02102 -0.0702 0.9990 0.0074
-12.250 -0.9433 0.02375 0.01975 -0.0710 0.9895 0.0075
-12.000 -0.9138 0.02277 0.01865 -0.0729 0.9821 0.0076
-11.750 -0.8853 0.02169 0.01745 -0.0746 0.9684 0.0077
-11.500 -0.8550 0.02069 0.01631 -0.0765 0.9431 0.0078
-11.250 -0.8330 0.02007 0.01551 -0.0762 0.9014 0.0079
-11.000 -0.8235 0.01895 0.01413 -0.0739 0.8646 0.0081
-10.750 -0.8080 0.01823 0.01324 -0.0723 0.8378 0.0084
-10.500 -0.7887 0.01772 0.01259 -0.0712 0.8160 0.0086
-10.250 -0.7685 0.01722 0.01197 -0.0703 0.7974 0.0088
-10.000 -0.7464 0.01686 0.01150 -0.0696 0.7821 0.0090
-9.750 -0.7247 0.01637 0.01090 -0.0689 0.7683 0.0092
-9.500 -0.7025 0.01591 0.01034 -0.0682 0.7553 0.0095
-9.250 -0.6800 0.01543 0.00975 -0.0675 0.7434 0.0097
-9.000 -0.6569 0.01500 0.00922 -0.0669 0.7326 0.0099
-8.750 -0.6335 0.01457 0.00870 -0.0664 0.7227 0.0102
-8.500 -0.6096 0.01415 0.00817 -0.0659 0.7137 0.0104
-8.250 -0.5851 0.01382 0.00777 -0.0655 0.7049 0.0107
-8.000 -0.5600 0.01350 0.00737 -0.0651 0.6968 0.0110
-7.750 -0.5352 0.01316 0.00695 -0.0648 0.6898 0.0111
-7.500 -0.5098 0.01284 0.00657 -0.0644 0.6827 0.0112
-7.250 -0.4854 0.01243 0.00605 -0.0640 0.6760 0.0114
-7.000 -0.4609 0.01193 0.00548 -0.0635 0.6699 0.0118
-6.750 -0.4357 0.01156 0.00504 -0.0632 0.6637 0.0122
-6.500 -0.4098 0.01125 0.00468 -0.0629 0.6585 0.0127
-6.250 -0.3836 0.01098 0.00435 -0.0627 0.6527 0.0131
-6.000 -0.3572 0.01074 0.00406 -0.0625 0.6475 0.0135
-5.750 -0.3304 0.01052 0.00379 -0.0624 0.6429 0.0140
-5.500 -0.3035 0.01032 0.00355 -0.0623 0.6378 0.0146
-5.250 -0.2766 0.01014 0.00332 -0.0621 0.6331 0.0152
-5.000 -0.2493 0.00997 0.00311 -0.0621 0.6290 0.0155
-4.750 -0.2221 0.00977 0.00287 -0.0620 0.6245 0.0167
-4.500 -0.1950 0.00960 0.00267 -0.0619 0.6200 0.0183
-4.250 -0.1677 0.00944 0.00249 -0.0618 0.6161 0.0205
-4.000 -0.1409 0.00917 0.00229 -0.0617 0.6123 0.0360
-3.750 -0.1139 0.00895 0.00212 -0.0616 0.6080 0.0534
-3.500 -0.0868 0.00876 0.00197 -0.0615 0.6041 0.0711
-3.250 -0.0600 0.00851 0.00183 -0.0615 0.6007 0.1011
-3.000 -0.0328 0.00829 0.00170 -0.0614 0.5970 0.1300
-2.750 -0.0056 0.00809 0.00159 -0.0614 0.5930 0.1596
-2.500 0.0213 0.00788 0.00149 -0.0614 0.5893 0.1979
-2.250 0.0485 0.00767 0.00140 -0.0613 0.5860 0.2370
-2.000 0.0761 0.00751 0.00132 -0.0614 0.5824 0.2689
-1.750 0.1028 0.00725 0.00125 -0.0613 0.5785 0.3270
-1.500 0.1294 0.00702 0.00121 -0.0612 0.5750 0.3906
-1.250 0.1571 0.00692 0.00119 -0.0612 0.5717 0.4226
-1.000 0.1854 0.00687 0.00117 -0.0613 0.5680 0.4386
-0.750 0.2136 0.00683 0.00116 -0.0614 0.5642 0.4547
-0.500 0.2416 0.00681 0.00115 -0.0615 0.5606 0.4698
-0.250 0.2698 0.00679 0.00115 -0.0615 0.5571 0.4849
0.000 0.2981 0.00676 0.00116 -0.0616 0.5534 0.4996
0.250 0.3263 0.00674 0.00116 -0.0617 0.5494 0.5135
0.500 0.3543 0.00674 0.00118 -0.0618 0.5455 0.5264
0.750 0.3824 0.00672 0.00119 -0.0619 0.5418 0.5408
1.000 0.4106 0.00670 0.00122 -0.0619 0.5379 0.5572
1.250 0.4385 0.00669 0.00125 -0.0620 0.5335 0.5754
1.500 0.4662 0.00669 0.00128 -0.0620 0.5294 0.5944
1.750 0.4942 0.00666 0.00132 -0.0621 0.5254 0.6139
2.000 0.5220 0.00665 0.00137 -0.0621 0.5205 0.6338
2.250 0.5494 0.00666 0.00142 -0.0620 0.5154 0.6547
2.500 0.5771 0.00664 0.00148 -0.0620 0.5096 0.6764
2.750 0.6042 0.00665 0.00154 -0.0619 0.5022 0.6999
3.000 0.6313 0.00665 0.00161 -0.0618 0.4942 0.7251
3.250 0.6578 0.00667 0.00169 -0.0616 0.4861 0.7530
3.500 0.6844 0.00665 0.00177 -0.0614 0.4777 0.7849
3.750 0.7102 0.00666 0.00186 -0.0610 0.4688 0.8192
4.000 0.7349 0.00667 0.00197 -0.0603 0.4584 0.8590
4.250 0.7591 0.00667 0.00210 -0.0594 0.4480 0.9070
4.500 0.7881 0.00676 0.00223 -0.0597 0.4361 0.9483
5.000 0.8537 0.00715 0.00253 -0.0622 0.4026 0.9823
5.250 0.8875 0.00740 0.00270 -0.0637 0.3812 0.9895
5.500 0.9187 0.00772 0.00291 -0.0648 0.3546 0.9961
5.750 0.9453 0.00812 0.00318 -0.0649 0.3214 1.0000
6.000 0.9610 0.00877 0.00356 -0.0629 0.2713 1.0000
6.250 0.9754 0.00952 0.00403 -0.0607 0.2163 1.0000
6.500 0.9914 0.01018 0.00446 -0.0589 0.1739 1.0000
6.750 1.0103 0.01067 0.00482 -0.0575 0.1474 1.0000
7.000 1.0288 0.01118 0.00522 -0.0560 0.1220 1.0000
7.250 1.0480 0.01164 0.00558 -0.0547 0.1039 1.0000
7.500 1.0649 0.01221 0.00602 -0.0530 0.0809 1.0000
7.750 1.0831 0.01268 0.00642 -0.0516 0.0664 1.0000
8.000 1.1008 0.01316 0.00684 -0.0500 0.0536 1.0000
8.250 1.1161 0.01372 0.00733 -0.0481 0.0394 1.0000
8.500 1.1311 0.01425 0.00781 -0.0462 0.0297 1.0000
8.750 1.1436 0.01474 0.00826 -0.0437 0.0228 1.0000
9.000 1.1552 0.01525 0.00876 -0.0411 0.0175 1.0000
9.250 1.1630 0.01597 0.00943 -0.0381 0.0098 1.0000
9.500 1.1742 0.01659 0.01005 -0.0358 0.0072 1.0000
9.750 1.1872 0.01716 0.01066 -0.0338 0.0066 1.0000
10.000 1.1987 0.01785 0.01138 -0.0318 0.0055 1.0000
10.250 1.2114 0.01850 0.01207 -0.0300 0.0053 1.0000
10.500 1.2237 0.01922 0.01284 -0.0283 0.0051 1.0000
10.750 1.2348 0.02005 0.01371 -0.0266 0.0048 1.0000
11.000 1.2451 0.02099 0.01470 -0.0250 0.0046 1.0000
11.250 1.2554 0.02198 0.01573 -0.0235 0.0044 1.0000
11.500 1.2645 0.02311 0.01690 -0.0221 0.0040 1.0000
11.750 1.2716 0.02444 0.01832 -0.0206 0.0038 1.0000
12.000 1.2798 0.02575 0.01969 -0.0193 0.0037 1.0000
12.250 1.2891 0.02703 0.02102 -0.0183 0.0037 1.0000
12.500 1.2992 0.02827 0.02231 -0.0174 0.0035 1.0000
12.750 1.3069 0.02976 0.02386 -0.0164 0.0035 1.0000
13.000 1.3144 0.03130 0.02547 -0.0156 0.0034 1.0000
13.250 1.3211 0.03294 0.02717 -0.0148 0.0033 1.0000
13.500 1.3289 0.03452 0.02881 -0.0141 0.0032 1.0000
13.750 1.3339 0.03640 0.03076 -0.0134 0.0031 1.0000
14.000 1.3386 0.03832 0.03276 -0.0128 0.0031 1.0000
14.250 1.3439 0.04024 0.03475 -0.0123 0.0030 1.0000
14.500 1.3461 0.04253 0.03712 -0.0118 0.0030 1.0000
14.750 1.3501 0.04468 0.03934 -0.0114 0.0029 1.0000
15.000 1.3537 0.04694 0.04167 -0.0112 0.0029 1.0000
15.250 1.3550 0.04950 0.04432 -0.0110 0.0028 1.0000
15.500 1.3571 0.05207 0.04695 -0.0110 0.0027 1.0000
15.750 1.3583 0.05477 0.04973 -0.0111 0.0027 1.0000
16.000 1.3587 0.05768 0.05273 -0.0113 0.0027 1.0000
16.250 1.3584 0.06074 0.05587 -0.0117 0.0026 1.0000
16.500 1.3591 0.06373 0.05895 -0.0121 0.0026 1.0000
16.750 1.3577 0.06709 0.06239 -0.0128 0.0026 1.0000
17.000 1.3557 0.07061 0.06600 -0.0135 0.0025 1.0000
17.250 1.3502 0.07473 0.07023 -0.0146 0.0025 1.0000
17.500 1.3472 0.07857 0.07416 -0.0156 0.0025 1.0000
17.750 1.3415 0.08292 0.07861 -0.0170 0.0024 1.0000
18.000 1.3354 0.08746 0.08326 -0.0185 0.0024 1.0000
18.250 1.3312 0.09182 0.08772 -0.0201 0.0025 1.0000
18.500 1.3167 0.09792 0.09394 -0.0225 0.0023 1.0000
18.750 1.3097 0.10296 0.09908 -0.0247 0.0023 1.0000
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