EH 2.5/10 (eh2510-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 2.5/10 (eh2510-il) Reynolds number: 200,000 Max Cl/Cd: 65.18 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh2510-il-200000.txt Download as CSV file: xf-eh2510-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.5/10
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4835 0.10009 0.09680 0.0004 1.0000 0.0437
-9.000 -0.4819 0.09630 0.09305 -0.0015 1.0000 0.0451
-7.500 -0.4661 0.05968 0.05678 -0.0206 1.0000 0.0520
-7.250 -0.4590 0.05620 0.05333 -0.0198 1.0000 0.0532
-7.000 -0.4552 0.05248 0.04959 -0.0198 1.0000 0.0547
-6.750 -0.4521 0.04844 0.04549 -0.0201 1.0000 0.0564
-6.500 -0.4481 0.04423 0.04117 -0.0205 1.0000 0.0596
-6.250 -0.4519 0.03920 0.03551 -0.0204 1.0000 0.0638
-6.000 -0.4387 0.03496 0.03154 -0.0203 1.0000 0.0661
-5.750 -0.4264 0.03215 0.02872 -0.0195 1.0000 0.0684
-5.500 -0.4044 0.02846 0.02479 -0.0209 0.9810 0.0736
-5.250 -0.3750 0.02297 0.01888 -0.0239 0.9441 0.0797
-5.000 -0.3986 0.03050 0.02522 -0.0152 0.9760 0.0485
-4.750 -0.3633 0.02362 0.01735 -0.0164 0.9492 0.0410
-4.500 -0.3236 0.02199 0.01552 -0.0188 0.9177 0.0438
-4.250 -0.2921 0.01963 0.01265 -0.0187 0.8853 0.0433
-4.000 -0.2661 0.01818 0.01085 -0.0175 0.8548 0.0439
-3.750 -0.2416 0.01710 0.00949 -0.0161 0.8276 0.0454
-3.500 -0.2170 0.01620 0.00837 -0.0149 0.8033 0.0477
-3.250 -0.1928 0.01542 0.00739 -0.0136 0.7826 0.0515
-3.000 -0.1693 0.01468 0.00661 -0.0126 0.7623 0.0579
-2.750 -0.1463 0.01390 0.00576 -0.0112 0.7444 0.0677
-2.500 -0.1233 0.01328 0.00512 -0.0100 0.7279 0.0934
-2.250 -0.0997 0.01290 0.00476 -0.0091 0.7124 0.1238
-2.000 -0.0761 0.01251 0.00443 -0.0082 0.6976 0.1603
-1.750 -0.0558 0.01172 0.00408 -0.0070 0.6838 0.2622
-1.500 -0.0517 0.00973 0.00431 -0.0010 0.6721 0.8487
-1.250 -0.0102 0.01018 0.00464 -0.0017 0.6582 0.9217
-1.000 0.0532 0.01073 0.00490 -0.0075 0.6429 0.9490
-0.750 0.1139 0.01112 0.00502 -0.0135 0.6282 0.9684
-0.500 0.1866 0.01129 0.00492 -0.0223 0.6129 0.9848
-0.250 0.2556 0.01111 0.00452 -0.0308 0.5981 1.0000
0.000 0.2777 0.01110 0.00440 -0.0299 0.5870 1.0000
0.250 0.2999 0.01111 0.00430 -0.0291 0.5768 1.0000
0.500 0.3221 0.01114 0.00419 -0.0282 0.5672 1.0000
0.750 0.3446 0.01114 0.00415 -0.0274 0.5566 1.0000
1.000 0.3671 0.01118 0.00411 -0.0266 0.5472 1.0000
1.250 0.3897 0.01124 0.00406 -0.0257 0.5384 1.0000
1.500 0.4124 0.01127 0.00406 -0.0249 0.5285 1.0000
1.750 0.4352 0.01135 0.00407 -0.0241 0.5199 1.0000
2.000 0.4581 0.01141 0.00407 -0.0233 0.5111 1.0000
2.250 0.4810 0.01149 0.00413 -0.0225 0.5020 1.0000
2.500 0.5039 0.01160 0.00416 -0.0216 0.4943 1.0000
2.750 0.5267 0.01168 0.00425 -0.0208 0.4851 1.0000
3.000 0.5495 0.01182 0.00435 -0.0199 0.4772 1.0000
3.250 0.5724 0.01194 0.00446 -0.0191 0.4690 1.0000
3.500 0.5951 0.01208 0.00461 -0.0182 0.4608 1.0000
3.750 0.6180 0.01224 0.00471 -0.0173 0.4532 1.0000
4.000 0.6408 0.01240 0.00492 -0.0165 0.4446 1.0000
4.250 0.6638 0.01260 0.00507 -0.0156 0.4375 1.0000
4.500 0.6866 0.01275 0.00530 -0.0147 0.4288 1.0000
4.750 0.7096 0.01297 0.00549 -0.0139 0.4215 1.0000
5.000 0.7326 0.01315 0.00572 -0.0130 0.4132 1.0000
5.250 0.7557 0.01338 0.00600 -0.0122 0.4056 1.0000
5.500 0.7788 0.01359 0.00621 -0.0114 0.3976 1.0000
5.750 0.8019 0.01382 0.00652 -0.0105 0.3893 1.0000
6.000 0.8253 0.01407 0.00674 -0.0098 0.3819 1.0000
6.250 0.8483 0.01431 0.00711 -0.0089 0.3732 1.0000
6.500 0.8717 0.01459 0.00740 -0.0082 0.3656 1.0000
6.750 0.8947 0.01481 0.00773 -0.0074 0.3565 1.0000
7.000 0.9178 0.01510 0.00811 -0.0066 0.3480 1.0000
7.250 0.9411 0.01537 0.00839 -0.0058 0.3396 1.0000
7.500 0.9632 0.01552 0.00868 -0.0048 0.3276 1.0000
7.750 0.9845 0.01556 0.00872 -0.0037 0.3113 1.0000
8.000 1.0054 0.01559 0.00888 -0.0027 0.2914 1.0000
8.250 1.0266 0.01577 0.00913 -0.0017 0.2728 1.0000
8.500 1.0475 0.01607 0.00947 -0.0007 0.2532 1.0000
8.750 1.0673 0.01645 0.00992 0.0003 0.2231 1.0000
9.000 1.0788 0.01767 0.01076 0.0021 0.1477 1.0000
9.250 1.0687 0.02108 0.01328 0.0059 0.0465 1.0000
9.500 1.0732 0.02293 0.01518 0.0085 0.0350 1.0000
9.750 1.0796 0.02441 0.01678 0.0108 0.0302 1.0000
10.000 1.0737 0.02649 0.01893 0.0141 0.0271 1.0000
10.250 1.0744 0.02785 0.02043 0.0169 0.0254 1.0000
10.500 1.0709 0.02973 0.02242 0.0191 0.0240 1.0000
10.750 1.0682 0.03195 0.02473 0.0204 0.0230 1.0000
11.000 1.0657 0.03446 0.02732 0.0210 0.0221 1.0000
11.250 1.0649 0.03699 0.02993 0.0215 0.0216 1.0000
11.500 1.0634 0.03968 0.03266 0.0221 0.0209 1.0000
11.750 1.0647 0.04216 0.03516 0.0233 0.0202 1.0000
12.000 1.0739 0.04431 0.03738 0.0256 0.0196 1.0000
12.250 1.0832 0.04660 0.03979 0.0268 0.0193 1.0000
12.500 1.0897 0.04898 0.04234 0.0273 0.0191 1.0000
12.750 1.0914 0.05167 0.04522 0.0273 0.0185 1.0000
13.000 1.0947 0.05453 0.04825 0.0274 0.0184 1.0000
13.250 1.0931 0.05769 0.05161 0.0269 0.0179 1.0000
13.500 1.0905 0.06116 0.05527 0.0262 0.0177 1.0000
13.750 1.0852 0.06492 0.05922 0.0250 0.0172 1.0000
14.000 1.0783 0.06923 0.06373 0.0238 0.0173 1.0000
14.250 1.0691 0.07387 0.06857 0.0221 0.0174 1.0000
14.500 1.0571 0.07909 0.07400 0.0199 0.0175 1.0000
14.750 1.0438 0.08464 0.07973 0.0173 0.0176 1.0000
15.000 1.0283 0.09083 0.08612 0.0140 0.0176 1.0000
15.250 1.0130 0.09733 0.09280 0.0105 0.0178 1.0000
15.500 0.9950 0.10469 0.10033 0.0062 0.0179 1.0000
15.750 0.9787 0.11208 0.10788 0.0019 0.0182 1.0000
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Polar data table (+)
Polar graphs
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