EPPLER 473 AIRFOIL (e473-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 473 AIRFOIL (e473-il) Reynolds number: 200,000 Max Cl/Cd: 47.92 at α=11° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e473-il-200000.txt Download as CSV file: xf-e473-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 473 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-18.000 -1.1138 0.09237 0.08743 -0.0268 1.0000 0.0816
-17.750 -1.1362 0.08556 0.08046 -0.0303 1.0000 0.0841
-17.500 -1.1527 0.07994 0.07474 -0.0330 1.0000 0.0868
-17.250 -1.1545 0.07682 0.07169 -0.0342 1.0000 0.0901
-17.000 -1.1707 0.07141 0.06618 -0.0369 1.0000 0.0931
-16.750 -1.1929 0.06529 0.05987 -0.0400 1.0000 0.0956
-16.500 -1.1999 0.06170 0.05631 -0.0412 1.0000 0.0990
-16.250 -1.2102 0.05759 0.05218 -0.0429 1.0000 0.1021
-16.000 -1.2246 0.05293 0.04738 -0.0450 1.0000 0.1052
-15.750 -1.2412 0.04815 0.04237 -0.0472 1.0000 0.1081
-15.500 -1.2430 0.04555 0.03988 -0.0476 1.0000 0.1119
-15.250 -1.2505 0.04230 0.03655 -0.0485 1.0000 0.1154
-15.000 -1.2601 0.03908 0.03313 -0.0491 1.0000 0.1191
-14.750 -1.2625 0.03685 0.03090 -0.0486 1.0000 0.1229
-14.500 -1.2646 0.03492 0.02893 -0.0479 1.0000 0.1267
-14.250 -1.2689 0.03305 0.02690 -0.0466 1.0000 0.1310
-14.000 -1.2691 0.03156 0.02536 -0.0448 1.0000 0.1349
-13.750 -1.2669 0.03053 0.02433 -0.0427 1.0000 0.1391
-13.500 -1.2673 0.02951 0.02317 -0.0399 1.0000 0.1436
-13.250 -1.2656 0.02859 0.02218 -0.0369 1.0000 0.1480
-13.000 -1.2607 0.02807 0.02171 -0.0338 1.0000 0.1523
-12.750 -1.2598 0.02752 0.02105 -0.0300 1.0000 0.1569
-12.500 -1.2539 0.02686 0.02031 -0.0269 1.0000 0.1617
-12.250 -1.2418 0.02658 0.02009 -0.0245 1.0000 0.1664
-12.000 -1.2329 0.02614 0.01950 -0.0216 1.0000 0.1716
-11.750 -1.2199 0.02560 0.01893 -0.0194 1.0000 0.1763
-11.500 -1.2036 0.02541 0.01877 -0.0175 1.0000 0.1808
-11.250 -1.1910 0.02502 0.01824 -0.0150 1.0000 0.1859
-11.000 -1.1754 0.02453 0.01769 -0.0131 1.0000 0.1905
-10.750 -1.1561 0.02438 0.01759 -0.0115 1.0000 0.1947
-10.500 -1.1402 0.02409 0.01719 -0.0094 1.0000 0.1997
-10.250 -1.1249 0.02359 0.01655 -0.0074 1.0000 0.2043
-10.000 -1.1032 0.02343 0.01649 -0.0062 1.0000 0.2083
-9.750 -1.0843 0.02323 0.01624 -0.0045 1.0000 0.2130
-9.500 -1.0701 0.02289 0.01565 -0.0021 1.0000 0.2178
-9.250 -1.0473 0.02245 0.01533 -0.0011 1.0000 0.2217
-9.000 -1.0259 0.02229 0.01520 0.0002 1.0000 0.2258
-8.750 -1.0074 0.02200 0.01478 0.0020 1.0000 0.2306
-8.500 -0.9899 0.02153 0.01415 0.0038 1.0000 0.2348
-8.250 -0.9666 0.02122 0.01395 0.0047 1.0000 0.2386
-8.000 -0.9453 0.02099 0.01372 0.0061 1.0000 0.2426
-7.750 -0.9262 0.02067 0.01328 0.0078 1.0000 0.2471
-7.500 -0.9070 0.02021 0.01270 0.0094 1.0000 0.2513
-7.250 -0.8840 0.01987 0.01246 0.0104 1.0000 0.2549
-7.000 -0.8625 0.01962 0.01221 0.0117 1.0000 0.2589
-6.750 -0.8427 0.01933 0.01183 0.0132 1.0000 0.2633
-6.500 -0.8233 0.01897 0.01134 0.0148 1.0000 0.2673
-6.250 -0.8007 0.01855 0.01102 0.0159 1.0000 0.2709
-6.000 -0.7793 0.01832 0.01082 0.0172 1.0000 0.2748
-5.750 -0.7592 0.01808 0.01052 0.0186 1.0000 0.2792
-5.500 -0.7402 0.01787 0.01018 0.0203 1.0000 0.2831
-5.250 -0.7188 0.01740 0.00979 0.0214 1.0000 0.2867
-5.000 -0.6983 0.01718 0.00964 0.0228 1.0000 0.2903
-4.750 -0.6698 0.01702 0.00946 0.0225 0.9978 0.2951
-4.500 -0.6189 0.01687 0.00917 0.0179 0.9886 0.3005
-4.250 -0.5686 0.01640 0.00885 0.0135 0.9797 0.3057
-4.000 -0.5211 0.01609 0.00858 0.0097 0.9678 0.3114
-3.750 -0.4806 0.01574 0.00815 0.0076 0.9499 0.3167
-3.500 -0.4396 0.01518 0.00767 0.0053 0.9288 0.3215
-3.250 -0.3892 0.01478 0.00732 0.0013 0.9043 0.3275
-3.000 -0.3275 0.01445 0.00685 -0.0049 0.8602 0.3345
-2.750 -0.2734 0.01411 0.00635 -0.0096 0.7801 0.3404
-2.500 -0.2462 0.01421 0.00614 -0.0088 0.7010 0.3457
-2.250 -0.2238 0.01437 0.00593 -0.0073 0.6359 0.3510
-2.000 -0.2009 0.01438 0.00573 -0.0060 0.5837 0.3557
-1.750 -0.1772 0.01443 0.00562 -0.0049 0.5424 0.3608
-1.500 -0.1532 0.01453 0.00551 -0.0039 0.5110 0.3670
-1.250 -0.1283 0.01451 0.00539 -0.0031 0.4850 0.3731
-1.000 -0.1032 0.01453 0.00533 -0.0024 0.4646 0.3795
-0.750 -0.0776 0.01458 0.00526 -0.0018 0.4478 0.3867
-0.500 -0.0518 0.01453 0.00522 -0.0012 0.4343 0.3938
-0.250 -0.0260 0.01461 0.00520 -0.0006 0.4230 0.4027
0.000 0.0000 0.01453 0.00519 0.0000 0.4119 0.4119
0.250 0.0260 0.01461 0.00520 0.0006 0.4028 0.4230
0.500 0.0517 0.01453 0.00522 0.0012 0.3938 0.4342
0.750 0.0775 0.01458 0.00526 0.0017 0.3868 0.4479
1.000 0.1031 0.01453 0.00533 0.0024 0.3795 0.4646
1.250 0.1283 0.01451 0.00539 0.0031 0.3731 0.4850
1.500 0.1532 0.01453 0.00551 0.0039 0.3670 0.5107
1.750 0.1772 0.01443 0.00562 0.0049 0.3608 0.5424
2.000 0.2009 0.01438 0.00573 0.0060 0.3557 0.5836
2.250 0.2238 0.01437 0.00594 0.0073 0.3510 0.6358
2.500 0.2462 0.01420 0.00613 0.0088 0.3457 0.7009
2.750 0.2734 0.01411 0.00635 0.0096 0.3403 0.7799
3.000 0.3274 0.01445 0.00685 0.0049 0.3345 0.8602
3.250 0.3891 0.01478 0.00732 -0.0013 0.3275 0.9043
3.500 0.4396 0.01517 0.00767 -0.0054 0.3214 0.9289
3.750 0.4806 0.01574 0.00815 -0.0076 0.3167 0.9500
4.000 0.5212 0.01609 0.00858 -0.0098 0.3115 0.9680
4.250 0.5686 0.01639 0.00884 -0.0135 0.3057 0.9797
4.500 0.6188 0.01686 0.00917 -0.0179 0.3005 0.9886
4.750 0.6698 0.01701 0.00946 -0.0225 0.2950 0.9978
5.000 0.6982 0.01718 0.00964 -0.0228 0.2903 1.0000
5.250 0.7187 0.01739 0.00978 -0.0214 0.2866 1.0000
5.500 0.7401 0.01787 0.01018 -0.0203 0.2831 1.0000
5.750 0.7592 0.01808 0.01053 -0.0186 0.2792 1.0000
6.000 0.7793 0.01832 0.01082 -0.0171 0.2748 1.0000
6.250 0.8006 0.01855 0.01102 -0.0159 0.2709 1.0000
6.500 0.8232 0.01896 0.01133 -0.0148 0.2673 1.0000
6.750 0.8427 0.01934 0.01183 -0.0132 0.2633 1.0000
7.000 0.8625 0.01962 0.01221 -0.0117 0.2589 1.0000
7.250 0.8839 0.01987 0.01247 -0.0104 0.2549 1.0000
7.500 0.9069 0.02021 0.01270 -0.0094 0.2513 1.0000
7.750 0.9262 0.02067 0.01327 -0.0078 0.2472 1.0000
8.000 0.9452 0.02099 0.01371 -0.0061 0.2426 1.0000
8.250 0.9665 0.02121 0.01394 -0.0047 0.2385 1.0000
8.500 0.9898 0.02153 0.01415 -0.0038 0.2349 1.0000
8.750 1.0074 0.02199 0.01477 -0.0019 0.2305 1.0000
9.000 1.0258 0.02230 0.01520 -0.0002 0.2259 1.0000
9.250 1.0472 0.02245 0.01533 0.0011 0.2218 1.0000
9.500 1.0700 0.02288 0.01565 0.0021 0.2178 1.0000
9.750 1.0843 0.02323 0.01624 0.0045 0.2130 1.0000
10.000 1.1032 0.02343 0.01649 0.0061 0.2083 1.0000
10.250 1.1249 0.02359 0.01655 0.0074 0.2043 1.0000
10.500 1.1402 0.02408 0.01719 0.0094 0.1997 1.0000
10.750 1.1561 0.02438 0.01759 0.0115 0.1947 1.0000
11.000 1.1755 0.02453 0.01769 0.0131 0.1904 1.0000
11.250 1.1911 0.02502 0.01824 0.0150 0.1859 1.0000
11.500 1.2037 0.02540 0.01876 0.0174 0.1808 1.0000
11.750 1.2200 0.02560 0.01893 0.0194 0.1762 1.0000
12.000 1.2331 0.02614 0.01950 0.0216 0.1716 1.0000
12.250 1.2420 0.02658 0.02008 0.0245 0.1664 1.0000
12.500 1.2541 0.02686 0.02031 0.0268 0.1616 1.0000
12.750 1.2602 0.02752 0.02105 0.0299 0.1569 1.0000
13.000 1.2612 0.02807 0.02171 0.0338 0.1523 1.0000
13.250 1.2662 0.02858 0.02217 0.0368 0.1479 1.0000
13.500 1.2679 0.02951 0.02317 0.0398 0.1436 1.0000
13.750 1.2675 0.03052 0.02431 0.0426 0.1390 1.0000
14.000 1.2699 0.03155 0.02534 0.0447 0.1348 1.0000
14.250 1.2693 0.03305 0.02690 0.0465 0.1308 1.0000
14.500 1.2656 0.03490 0.02891 0.0478 0.1267 1.0000
14.750 1.2636 0.03682 0.03086 0.0485 0.1228 1.0000
15.000 1.2611 0.03906 0.03311 0.0489 0.1190 1.0000
15.250 1.2518 0.04226 0.03650 0.0484 0.1154 1.0000
15.500 1.2443 0.04552 0.03985 0.0474 0.1118 1.0000
15.750 1.2426 0.04811 0.04232 0.0470 0.1080 1.0000
16.000 1.2263 0.05288 0.04733 0.0449 0.1051 1.0000
16.250 1.2116 0.05757 0.05215 0.0427 0.1019 1.0000
16.500 1.2021 0.06158 0.05618 0.0410 0.0988 1.0000
16.750 1.1943 0.06531 0.05989 0.0397 0.0956 1.0000
17.000 1.1727 0.07134 0.06612 0.0366 0.0930 1.0000
17.250 1.1572 0.07664 0.07150 0.0340 0.0900 1.0000
17.500 1.1565 0.07959 0.07437 0.0330 0.0866 1.0000
17.750 1.1377 0.08561 0.08051 0.0300 0.0840 1.0000
18.000 1.1157 0.09236 0.08741 0.0265 0.0814 1.0000
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