E197 (13.49%) (e197-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E197 (13.49%) (e197-il) Reynolds number: 100,000 Max Cl/Cd: 53.22 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e197-il-100000-n5.txt Download as CSV file: xf-e197-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5675 0.05917 0.05388 -0.0708 1.0000 0.0272
-10.250 -0.5873 0.05553 0.05014 -0.0715 1.0000 0.0272
-10.000 -0.6094 0.05279 0.04731 -0.0694 1.0000 0.0271
-9.750 -0.6267 0.05021 0.04458 -0.0667 1.0000 0.0271
-9.500 -0.6414 0.04764 0.04183 -0.0636 1.0000 0.0271
-9.250 -0.6537 0.04534 0.03933 -0.0601 1.0000 0.0272
-9.000 -0.6448 0.04177 0.03538 -0.0610 0.9907 0.0274
-8.750 -0.6225 0.03825 0.03152 -0.0634 0.9784 0.0280
-8.500 -0.5966 0.03553 0.02850 -0.0655 0.9665 0.0286
-8.250 -0.5679 0.03359 0.02633 -0.0675 0.9553 0.0302
-8.000 -0.5403 0.03169 0.02413 -0.0688 0.9425 0.0320
-7.750 -0.5125 0.02968 0.02178 -0.0698 0.9297 0.0333
-7.500 -0.4837 0.02782 0.01960 -0.0705 0.9174 0.0343
-7.250 -0.4544 0.02626 0.01778 -0.0712 0.9056 0.0353
-7.000 -0.4271 0.02470 0.01614 -0.0717 0.8940 0.0368
-6.750 -0.4001 0.02355 0.01489 -0.0720 0.8826 0.0387
-6.500 -0.3750 0.02264 0.01385 -0.0718 0.8701 0.0419
-6.250 -0.3507 0.02181 0.01283 -0.0713 0.8580 0.0461
-6.000 -0.3281 0.02090 0.01186 -0.0707 0.8467 0.0510
-5.750 -0.3048 0.02007 0.01089 -0.0700 0.8365 0.0585
-5.500 -0.2824 0.01923 0.01005 -0.0693 0.8261 0.0728
-5.250 -0.2596 0.01851 0.00938 -0.0687 0.8162 0.0995
-5.000 -0.2356 0.01786 0.00880 -0.0683 0.8079 0.1385
-4.750 -0.2136 0.01716 0.00838 -0.0678 0.7986 0.1985
-4.500 -0.1910 0.01654 0.00801 -0.0672 0.7906 0.2647
-4.250 -0.1676 0.01611 0.00775 -0.0666 0.7827 0.3235
-4.000 -0.1434 0.01585 0.00759 -0.0659 0.7753 0.3796
-3.750 -0.1186 0.01569 0.00744 -0.0652 0.7679 0.4283
-3.500 -0.0934 0.01559 0.00731 -0.0646 0.7612 0.4667
-3.250 -0.0681 0.01552 0.00720 -0.0640 0.7542 0.4985
-3.000 -0.0421 0.01545 0.00705 -0.0634 0.7484 0.5263
-2.750 -0.0168 0.01541 0.00697 -0.0629 0.7414 0.5519
-2.500 0.0095 0.01535 0.00686 -0.0623 0.7360 0.5755
-2.250 0.0350 0.01532 0.00681 -0.0618 0.7295 0.5984
-2.000 0.0610 0.01527 0.00673 -0.0613 0.7238 0.6203
-1.750 0.0875 0.01524 0.00665 -0.0608 0.7187 0.6423
-1.500 0.1130 0.01522 0.00665 -0.0603 0.7124 0.6634
-1.250 0.1397 0.01519 0.00657 -0.0598 0.7074 0.6864
-1.000 0.1658 0.01518 0.00659 -0.0593 0.7020 0.7093
-0.750 0.1917 0.01518 0.00661 -0.0588 0.6964 0.7340
-0.500 0.2186 0.01516 0.00658 -0.0583 0.6919 0.7600
-0.250 0.2446 0.01519 0.00666 -0.0577 0.6863 0.7869
0.000 0.2721 0.01521 0.00672 -0.0574 0.6810 0.8157
0.250 0.3030 0.01523 0.00672 -0.0576 0.6768 0.8456
0.500 0.3358 0.01533 0.00685 -0.0585 0.6712 0.8762
0.750 0.3736 0.01541 0.00693 -0.0604 0.6660 0.9051
1.000 0.4143 0.01548 0.00692 -0.0629 0.6619 0.9315
1.250 0.4533 0.01562 0.00707 -0.0655 0.6560 0.9570
1.500 0.4952 0.01572 0.00713 -0.0686 0.6508 0.9782
1.750 0.5389 0.01577 0.00711 -0.0720 0.6468 0.9958
2.000 0.5629 0.01598 0.00735 -0.0719 0.6406 1.0000
2.250 0.5845 0.01616 0.00749 -0.0710 0.6356 1.0000
2.500 0.6081 0.01631 0.00757 -0.0703 0.6316 1.0000
2.750 0.6280 0.01659 0.00790 -0.0691 0.6253 1.0000
3.000 0.6510 0.01678 0.00809 -0.0683 0.6204 1.0000
3.250 0.6749 0.01697 0.00827 -0.0677 0.6158 1.0000
3.500 0.6959 0.01727 0.00863 -0.0667 0.6096 1.0000
3.750 0.7203 0.01745 0.00881 -0.0661 0.6047 1.0000
4.000 0.7431 0.01771 0.00913 -0.0653 0.5992 1.0000
4.250 0.7658 0.01797 0.00944 -0.0645 0.5929 1.0000
4.500 0.7921 0.01809 0.00956 -0.0641 0.5881 1.0000
4.750 0.8123 0.01842 0.01001 -0.0629 0.5802 1.0000
5.000 0.8383 0.01851 0.01013 -0.0625 0.5742 1.0000
5.250 0.8591 0.01879 0.01053 -0.0614 0.5656 1.0000
5.500 0.8856 0.01882 0.01057 -0.0609 0.5589 1.0000
5.750 0.9057 0.01909 0.01098 -0.0596 0.5492 1.0000
6.000 0.9291 0.01920 0.01119 -0.0588 0.5404 1.0000
6.250 0.9529 0.01926 0.01131 -0.0579 0.5308 1.0000
6.500 0.9733 0.01945 0.01164 -0.0566 0.5194 1.0000
6.750 0.9946 0.01959 0.01188 -0.0554 0.5075 1.0000
7.000 1.0156 0.01971 0.01210 -0.0541 0.4945 1.0000
7.250 1.0358 0.01985 0.01236 -0.0527 0.4798 1.0000
7.500 1.0552 0.02001 0.01261 -0.0512 0.4632 1.0000
7.750 1.0739 0.02018 0.01284 -0.0496 0.4448 1.0000
8.000 1.0898 0.02050 0.01322 -0.0476 0.4228 1.0000
8.250 1.1043 0.02086 0.01359 -0.0454 0.3973 1.0000
8.500 1.1157 0.02138 0.01409 -0.0428 0.3661 1.0000
8.750 1.1231 0.02208 0.01467 -0.0398 0.3310 1.0000
9.000 1.1248 0.02300 0.01543 -0.0361 0.2952 1.0000
9.250 1.1229 0.02416 0.01642 -0.0321 0.2632 1.0000
9.500 1.1198 0.02558 0.01768 -0.0286 0.2335 1.0000
9.750 1.1172 0.02717 0.01916 -0.0256 0.2070 1.0000
10.000 1.1151 0.02891 0.02081 -0.0230 0.1841 1.0000
10.250 1.1134 0.03080 0.02263 -0.0209 0.1626 1.0000
10.500 1.1120 0.03282 0.02458 -0.0191 0.1439 1.0000
10.750 1.1114 0.03491 0.02666 -0.0176 0.1257 1.0000
11.000 1.1097 0.03721 0.02887 -0.0163 0.1081 1.0000
11.500 1.1083 0.04192 0.03344 -0.0143 0.0781 1.0000
11.750 1.1084 0.04434 0.03582 -0.0135 0.0659 1.0000
12.000 1.1079 0.04688 0.03833 -0.0129 0.0563 1.0000
12.250 1.1095 0.04929 0.04082 -0.0123 0.0485 1.0000
12.500 1.1082 0.05206 0.04363 -0.0118 0.0426 1.0000
12.750 1.1069 0.05493 0.04655 -0.0115 0.0376 1.0000
13.000 1.1045 0.05799 0.04967 -0.0112 0.0335 1.0000
13.250 1.1037 0.06099 0.05277 -0.0112 0.0297 1.0000
13.500 1.1006 0.06433 0.05616 -0.0113 0.0278 1.0000
13.750 1.0996 0.06752 0.05950 -0.0114 0.0256 1.0000
14.000 1.1000 0.07062 0.06275 -0.0116 0.0240 1.0000
14.250 1.0993 0.07394 0.06618 -0.0120 0.0226 1.0000
14.500 1.0981 0.07740 0.06974 -0.0125 0.0217 1.0000
14.750 1.0968 0.08093 0.07336 -0.0131 0.0210 1.0000
15.000 1.0961 0.08437 0.07687 -0.0136 0.0203 1.0000
15.250 1.0979 0.08764 0.08033 -0.0139 0.0196 1.0000
15.500 1.0988 0.09112 0.08399 -0.0145 0.0190 1.0000
15.750 1.0987 0.09483 0.08789 -0.0153 0.0185 1.0000
16.000 1.0972 0.09886 0.09210 -0.0165 0.0181 1.0000
16.250 1.0939 0.10330 0.09671 -0.0180 0.0176 1.0000
16.500 1.0894 0.10802 0.10161 -0.0198 0.0173 1.0000
16.750 1.0838 0.11310 0.10686 -0.0220 0.0170 1.0000
17.000 1.0771 0.11847 0.11239 -0.0247 0.0166 1.0000
17.250 1.0699 0.12407 0.11811 -0.0277 0.0162 1.0000
17.500 1.0612 0.13021 0.12442 -0.0310 0.0161 1.0000
17.750 1.0526 0.13646 0.13081 -0.0345 0.0159 1.0000
18.000 1.0405 0.14390 0.13843 -0.0389 0.0159 1.0000
18.250 1.0064 0.15823 0.15314 -0.0476 0.0167 1.0000
18.500 0.9443 0.18464 0.17977 -0.0625 0.0182 1.0000
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Polar data table (+)
Polar graphs
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