E197 (13.49%) (e197-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E197 (13.49%) (e197-il) Reynolds number: 500,000 Max Cl/Cd: 110.66 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e197-il-500000.txt Download as CSV file: xf-e197-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.6448 0.04642 0.04349 -0.0760 1.0000 0.0168
-10.750 -0.6643 0.04342 0.04036 -0.0753 1.0000 0.0167
-10.500 -0.6910 0.04121 0.03802 -0.0708 1.0000 0.0167
-10.250 -0.7110 0.03858 0.03524 -0.0665 1.0000 0.0166
-10.000 -0.7118 0.03525 0.03161 -0.0659 0.9963 0.0166
-9.750 -0.6909 0.03191 0.02785 -0.0685 0.9878 0.0169
-9.500 -0.6677 0.02892 0.02440 -0.0708 0.9797 0.0174
-9.250 -0.6444 0.02496 0.02008 -0.0726 0.9707 0.0178
-9.000 -0.6174 0.02284 0.01778 -0.0738 0.9574 0.0181
-8.750 -0.5894 0.02128 0.01606 -0.0748 0.9402 0.0186
-8.500 -0.5635 0.01997 0.01458 -0.0749 0.9180 0.0190
-8.250 -0.5409 0.01896 0.01339 -0.0743 0.8938 0.0195
-8.000 -0.5199 0.01808 0.01230 -0.0732 0.8703 0.0200
-7.750 -0.4985 0.01735 0.01139 -0.0721 0.8499 0.0206
-7.500 -0.4763 0.01675 0.01063 -0.0712 0.8319 0.0214
-7.250 -0.4538 0.01612 0.00984 -0.0703 0.8162 0.0219
-7.000 -0.4309 0.01554 0.00911 -0.0694 0.8023 0.0222
-6.750 -0.4115 0.01442 0.00784 -0.0681 0.7897 0.0230
-6.500 -0.3897 0.01371 0.00702 -0.0672 0.7782 0.0239
-6.250 -0.3660 0.01321 0.00644 -0.0666 0.7678 0.0250
-6.000 -0.3416 0.01282 0.00596 -0.0661 0.7586 0.0264
-5.750 -0.3165 0.01248 0.00552 -0.0656 0.7495 0.0279
-5.500 -0.2919 0.01201 0.00495 -0.0650 0.7415 0.0299
-5.250 -0.2668 0.01162 0.00451 -0.0646 0.7339 0.0334
-5.000 -0.2414 0.01122 0.00409 -0.0642 0.7268 0.0423
-4.750 -0.2174 0.01064 0.00367 -0.0636 0.7198 0.0841
-4.500 -0.1922 0.01026 0.00341 -0.0634 0.7138 0.1241
-4.250 -0.1666 0.00989 0.00319 -0.0631 0.7074 0.1656
-4.000 -0.1410 0.00958 0.00298 -0.0629 0.7018 0.2098
-3.750 -0.1153 0.00922 0.00280 -0.0627 0.6960 0.2629
-3.500 -0.0896 0.00889 0.00265 -0.0625 0.6906 0.3206
-3.250 -0.0638 0.00866 0.00257 -0.0622 0.6857 0.3816
-3.000 -0.0371 0.00848 0.00252 -0.0621 0.6803 0.4295
-2.750 -0.0099 0.00840 0.00247 -0.0620 0.6753 0.4607
-2.500 0.0176 0.00838 0.00242 -0.0619 0.6709 0.4840
-2.250 0.0451 0.00830 0.00239 -0.0618 0.6659 0.5058
-2.000 0.0727 0.00826 0.00236 -0.0617 0.6612 0.5279
-1.750 0.1004 0.00824 0.00232 -0.0617 0.6570 0.5448
-1.500 0.1281 0.00821 0.00230 -0.0616 0.6526 0.5612
-1.250 0.1557 0.00816 0.00228 -0.0616 0.6479 0.5780
-1.000 0.1834 0.00813 0.00226 -0.0615 0.6437 0.5956
-0.750 0.2110 0.00813 0.00226 -0.0614 0.6398 0.6144
-0.500 0.2385 0.00807 0.00227 -0.0614 0.6352 0.6344
-0.250 0.2658 0.00802 0.00227 -0.0612 0.6309 0.6552
0.000 0.2932 0.00801 0.00228 -0.0611 0.6271 0.6785
0.250 0.3202 0.00796 0.00233 -0.0609 0.6229 0.7043
0.500 0.3469 0.00789 0.00236 -0.0606 0.6185 0.7342
0.750 0.3732 0.00782 0.00240 -0.0602 0.6144 0.7682
1.000 0.3993 0.00781 0.00246 -0.0597 0.6106 0.8057
1.250 0.4246 0.00771 0.00253 -0.0590 0.6063 0.8473
1.500 0.4507 0.00766 0.00261 -0.0583 0.6020 0.8904
1.750 0.4820 0.00770 0.00269 -0.0588 0.5979 0.9285
2.000 0.5182 0.00779 0.00277 -0.0605 0.5937 0.9547
2.250 0.5564 0.00784 0.00285 -0.0627 0.5889 0.9715
2.500 0.5960 0.00791 0.00289 -0.0652 0.5842 0.9824
2.750 0.6389 0.00800 0.00294 -0.0686 0.5795 0.9890
3.000 0.6803 0.00802 0.00300 -0.0716 0.5736 0.9960
3.250 0.7171 0.00807 0.00301 -0.0736 0.5678 1.0000
3.500 0.7400 0.00813 0.00308 -0.0728 0.5618 1.0000
3.750 0.7634 0.00817 0.00314 -0.0719 0.5556 1.0000
4.000 0.7871 0.00827 0.00320 -0.0711 0.5498 1.0000
4.250 0.8107 0.00831 0.00329 -0.0704 0.5428 1.0000
4.500 0.8346 0.00842 0.00336 -0.0696 0.5363 1.0000
4.750 0.8586 0.00846 0.00347 -0.0689 0.5287 1.0000
5.000 0.8824 0.00858 0.00355 -0.0681 0.5216 1.0000
5.250 0.9064 0.00863 0.00366 -0.0674 0.5126 1.0000
5.500 0.9302 0.00874 0.00378 -0.0666 0.5038 1.0000
5.750 0.9540 0.00885 0.00390 -0.0658 0.4941 1.0000
6.000 0.9780 0.00896 0.00404 -0.0651 0.4832 1.0000
6.250 1.0016 0.00910 0.00420 -0.0644 0.4708 1.0000
6.500 1.0247 0.00926 0.00436 -0.0635 0.4559 1.0000
6.750 1.0474 0.00947 0.00454 -0.0626 0.4388 1.0000
7.000 1.0691 0.00973 0.00477 -0.0616 0.4194 1.0000
7.250 1.0892 0.01009 0.00504 -0.0603 0.3904 1.0000
7.500 1.1059 0.01064 0.00542 -0.0585 0.3476 1.0000
7.750 1.1185 0.01144 0.00595 -0.0562 0.2937 1.0000
8.000 1.1285 0.01240 0.00661 -0.0535 0.2413 1.0000
8.250 1.1384 0.01333 0.00730 -0.0508 0.1968 1.0000
8.500 1.1485 0.01420 0.00797 -0.0482 0.1621 1.0000
8.750 1.1583 0.01500 0.00863 -0.0455 0.1345 1.0000
9.000 1.1664 0.01570 0.00925 -0.0425 0.1140 1.0000
9.250 1.1726 0.01650 0.00995 -0.0392 0.0954 1.0000
9.500 1.1795 0.01733 0.01071 -0.0363 0.0794 1.0000
9.750 1.1864 0.01822 0.01155 -0.0336 0.0653 1.0000
10.000 1.1931 0.01919 0.01248 -0.0311 0.0533 1.0000
10.250 1.1974 0.02037 0.01359 -0.0286 0.0407 1.0000
10.500 1.1965 0.02198 0.01511 -0.0258 0.0259 1.0000
10.750 1.1977 0.02361 0.01672 -0.0235 0.0190 1.0000
11.000 1.2018 0.02516 0.01832 -0.0217 0.0163 1.0000
11.250 1.2073 0.02669 0.01990 -0.0202 0.0145 1.0000
11.500 1.2095 0.02857 0.02183 -0.0187 0.0135 1.0000
11.750 1.2139 0.03034 0.02369 -0.0175 0.0128 1.0000
12.000 1.2189 0.03212 0.02555 -0.0164 0.0120 1.0000
12.250 1.2235 0.03398 0.02750 -0.0154 0.0118 1.0000
12.500 1.2274 0.03595 0.02955 -0.0146 0.0114 1.0000
12.750 1.2297 0.03812 0.03180 -0.0138 0.0110 1.0000
13.000 1.2285 0.04067 0.03442 -0.0130 0.0105 1.0000
13.250 1.2285 0.04317 0.03700 -0.0124 0.0104 1.0000
13.500 1.2184 0.04674 0.04067 -0.0117 0.0100 1.0000
13.750 1.2201 0.04924 0.04324 -0.0113 0.0099 1.0000
14.000 1.2240 0.05158 0.04569 -0.0111 0.0097 1.0000
14.250 1.2262 0.05416 0.04836 -0.0109 0.0094 1.0000
14.500 1.2279 0.05683 0.05112 -0.0109 0.0094 1.0000
14.750 1.2325 0.05928 0.05365 -0.0111 0.0091 1.0000
15.000 1.2325 0.06229 0.05676 -0.0112 0.0089 1.0000
15.250 1.2334 0.06526 0.05982 -0.0114 0.0087 1.0000
15.500 1.2349 0.06822 0.06288 -0.0118 0.0086 1.0000
15.750 1.2353 0.07141 0.06617 -0.0122 0.0085 1.0000
16.000 1.2351 0.07470 0.06956 -0.0127 0.0083 1.0000
16.250 1.2352 0.07806 0.07300 -0.0135 0.0081 1.0000
16.500 1.2348 0.08151 0.07656 -0.0142 0.0081 1.0000
16.750 1.2346 0.08506 0.08021 -0.0152 0.0081 1.0000
17.000 1.2323 0.08890 0.08413 -0.0162 0.0079 1.0000
17.250 1.2308 0.09274 0.08809 -0.0173 0.0079 1.0000
17.500 1.2284 0.09682 0.09229 -0.0187 0.0078 1.0000
17.750 1.2252 0.10108 0.09665 -0.0202 0.0078 1.0000
18.000 1.2207 0.10557 0.10127 -0.0218 0.0077 1.0000
18.250 1.2157 0.11036 0.10619 -0.0238 0.0077 1.0000
18.500 1.2090 0.11549 0.11146 -0.0261 0.0076 1.0000
18.750 1.2004 0.12109 0.11720 -0.0287 0.0076 1.0000
19.000 1.1923 0.12683 0.12310 -0.0317 0.0076 1.0000
19.250 1.1848 0.13269 0.12911 -0.0350 0.0077 1.0000
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Polar data table (+)
Polar graphs
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