EPPLER E838 HYDROFOIL AIRFOIL (e838-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER E838 HYDROFOIL AIRFOIL (e838-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.35 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e838-il-1000000.txt Download as CSV file: xf-e838-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E838 HYDROFOIL AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -1.0178 0.09079 0.08729 -0.0324 1.0000 0.0052
-18.250 -1.0319 0.08527 0.08161 -0.0343 1.0000 0.0053
-18.000 -1.0486 0.07967 0.07584 -0.0358 1.0000 0.0054
-17.750 -1.0423 0.07707 0.07319 -0.0369 1.0000 0.0053
-17.500 -1.0584 0.07190 0.06787 -0.0379 1.0000 0.0055
-17.250 -1.0638 0.06811 0.06399 -0.0388 1.0000 0.0057
-17.000 -1.0661 0.06480 0.06059 -0.0394 1.0000 0.0057
-16.750 -1.0649 0.06199 0.05768 -0.0399 1.0000 0.0056
-16.500 -1.0621 0.05936 0.05501 -0.0405 1.0000 0.0060
-16.250 -1.0608 0.05665 0.05222 -0.0407 1.0000 0.0060
-16.000 -1.0562 0.05436 0.04988 -0.0410 1.0000 0.0062
-15.750 -1.0517 0.05210 0.04755 -0.0411 1.0000 0.0063
-15.500 -1.0472 0.04992 0.04531 -0.0411 1.0000 0.0064
-15.250 -1.0390 0.04811 0.04345 -0.0411 1.0000 0.0066
-15.000 -1.0365 0.04584 0.04110 -0.0409 1.0000 0.0066
-14.750 -1.0316 0.04383 0.03901 -0.0406 1.0000 0.0068
-14.500 -1.0193 0.04252 0.03766 -0.0405 1.0000 0.0071
-14.250 -1.0171 0.04037 0.03544 -0.0399 1.0000 0.0071
-14.000 -1.0048 0.03911 0.03412 -0.0397 1.0000 0.0073
-13.750 -1.0030 0.03703 0.03197 -0.0390 1.0000 0.0072
-13.500 -0.9957 0.03544 0.03032 -0.0383 1.0000 0.0075
-13.250 -0.9965 0.03326 0.02807 -0.0372 1.0000 0.0079
-13.000 -0.9643 0.03133 0.02606 -0.0422 0.9416 0.0083
-12.750 -0.9402 0.03017 0.02461 -0.0443 0.8724 0.0086
-12.500 -0.9330 0.02913 0.02341 -0.0429 0.8441 0.0090
-12.250 -0.9231 0.02815 0.02232 -0.0417 0.8263 0.0094
-12.000 -0.9149 0.02703 0.02109 -0.0405 0.8131 0.0096
-11.750 -0.9009 0.02628 0.02025 -0.0397 0.8026 0.0101
-11.500 -0.8993 0.02474 0.01861 -0.0378 0.7930 0.0109
-11.250 -0.8902 0.02369 0.01750 -0.0365 0.7851 0.0114
-11.000 -0.8784 0.02283 0.01657 -0.0354 0.7775 0.0121
-10.750 -0.8661 0.02199 0.01568 -0.0343 0.7710 0.0127
-10.500 -0.8510 0.02133 0.01497 -0.0335 0.7648 0.0133
-10.250 -0.8452 0.02018 0.01374 -0.0316 0.7592 0.0148
-10.000 -0.8337 0.01933 0.01286 -0.0303 0.7541 0.0161
-9.750 -0.8200 0.01864 0.01212 -0.0291 0.7491 0.0171
-9.500 -0.8091 0.01785 0.01126 -0.0275 0.7442 0.0187
-9.250 -0.7983 0.01703 0.01044 -0.0259 0.7400 0.0212
-9.000 -0.7848 0.01639 0.00976 -0.0245 0.7356 0.0233
-8.750 -0.7751 0.01564 0.00899 -0.0226 0.7315 0.0274
-8.500 -0.7650 0.01494 0.00830 -0.0206 0.7277 0.0341
-8.250 -0.7563 0.01422 0.00762 -0.0183 0.7239 0.0447
-8.000 -0.7488 0.01354 0.00699 -0.0156 0.7200 0.0595
-7.750 -0.7431 0.01289 0.00641 -0.0124 0.7163 0.0774
-7.500 -0.7371 0.01237 0.00596 -0.0090 0.7128 0.0977
-7.250 -0.7315 0.01177 0.00551 -0.0055 0.7097 0.1279
-7.000 -0.7217 0.01112 0.00504 -0.0028 0.7065 0.1676
-6.750 -0.7127 0.01034 0.00451 0.0000 0.7033 0.2227
-6.500 -0.7035 0.00949 0.00396 0.0027 0.7000 0.2900
-6.250 -0.6937 0.00856 0.00341 0.0054 0.6971 0.3728
-6.000 -0.6775 0.00789 0.00304 0.0071 0.6944 0.4405
-5.750 -0.6546 0.00758 0.00284 0.0077 0.6916 0.4773
-5.500 -0.6291 0.00741 0.00270 0.0078 0.6888 0.4987
-5.250 -0.6027 0.00730 0.00259 0.0079 0.6859 0.5188
-5.000 -0.5757 0.00725 0.00251 0.0078 0.6829 0.5341
-4.750 -0.5482 0.00716 0.00245 0.0077 0.6806 0.5469
-4.500 -0.5203 0.00710 0.00238 0.0074 0.6780 0.5549
-4.250 -0.4918 0.00709 0.00233 0.0071 0.6753 0.5644
-4.000 -0.4639 0.00705 0.00230 0.0069 0.6727 0.5729
-3.750 -0.4354 0.00708 0.00225 0.0066 0.6699 0.5797
-3.500 -0.4071 0.00706 0.00223 0.0063 0.6672 0.5859
-3.250 -0.3781 0.00707 0.00221 0.0059 0.6649 0.5915
-3.000 -0.3494 0.00703 0.00216 0.0055 0.6623 0.5961
-2.750 -0.3205 0.00701 0.00213 0.0051 0.6596 0.6001
-2.500 -0.2915 0.00701 0.00209 0.0047 0.6570 0.6036
-2.250 -0.2625 0.00704 0.00206 0.0042 0.6543 0.6066
-2.000 -0.2334 0.00702 0.00202 0.0038 0.6519 0.6095
-1.750 -0.2043 0.00697 0.00199 0.0033 0.6495 0.6124
-1.500 -0.1751 0.00695 0.00197 0.0029 0.6468 0.6152
-1.250 -0.1459 0.00695 0.00195 0.0024 0.6441 0.6180
-1.000 -0.1167 0.00695 0.00192 0.0019 0.6416 0.6207
-0.750 -0.0876 0.00700 0.00191 0.0014 0.6389 0.6230
-0.500 -0.0585 0.00695 0.00190 0.0010 0.6365 0.6260
-0.250 -0.0293 0.00693 0.00190 0.0005 0.6339 0.6287
0.000 0.0000 0.00692 0.00190 0.0000 0.6311 0.6312
0.250 0.0293 0.00693 0.00190 -0.0005 0.6286 0.6339
0.500 0.0585 0.00695 0.00190 -0.0010 0.6260 0.6365
0.750 0.0875 0.00700 0.00191 -0.0014 0.6229 0.6390
1.000 0.1167 0.00695 0.00192 -0.0019 0.6206 0.6417
1.250 0.1459 0.00695 0.00195 -0.0024 0.6179 0.6442
1.500 0.1751 0.00695 0.00197 -0.0028 0.6151 0.6468
1.750 0.2043 0.00697 0.00199 -0.0033 0.6123 0.6495
2.000 0.2334 0.00702 0.00202 -0.0038 0.6094 0.6519
2.250 0.2625 0.00703 0.00206 -0.0042 0.6066 0.6544
2.500 0.2915 0.00701 0.00209 -0.0047 0.6036 0.6570
2.750 0.3205 0.00701 0.00213 -0.0051 0.6000 0.6597
3.000 0.3493 0.00703 0.00216 -0.0055 0.5961 0.6623
3.250 0.3781 0.00707 0.00221 -0.0059 0.5915 0.6649
3.500 0.4070 0.00706 0.00223 -0.0063 0.5858 0.6672
3.750 0.4354 0.00708 0.00225 -0.0066 0.5798 0.6698
4.000 0.4639 0.00706 0.00230 -0.0069 0.5729 0.6726
4.250 0.4918 0.00709 0.00233 -0.0071 0.5644 0.6753
4.500 0.5202 0.00710 0.00238 -0.0074 0.5551 0.6780
4.750 0.5482 0.00716 0.00245 -0.0077 0.5469 0.6806
5.000 0.5756 0.00725 0.00251 -0.0078 0.5343 0.6829
5.250 0.6026 0.00730 0.00259 -0.0079 0.5188 0.6859
5.500 0.6290 0.00741 0.00270 -0.0078 0.4990 0.6888
5.750 0.6545 0.00758 0.00284 -0.0076 0.4772 0.6916
6.000 0.6772 0.00791 0.00304 -0.0070 0.4387 0.6944
6.250 0.6935 0.00857 0.00341 -0.0054 0.3723 0.6971
6.500 0.7037 0.00948 0.00396 -0.0028 0.2916 0.7001
6.750 0.7127 0.01034 0.00451 0.0000 0.2232 0.7033
7.000 0.7217 0.01111 0.00504 0.0028 0.1677 0.7066
7.250 0.7297 0.01183 0.00554 0.0057 0.1245 0.7098
7.500 0.7375 0.01236 0.00595 0.0089 0.0984 0.7128
7.750 0.7428 0.01289 0.00641 0.0124 0.0772 0.7163
8.000 0.7489 0.01353 0.00699 0.0156 0.0596 0.7200
8.250 0.7565 0.01421 0.00762 0.0183 0.0451 0.7239
8.500 0.7652 0.01493 0.00830 0.0206 0.0342 0.7277
8.750 0.7755 0.01562 0.00898 0.0225 0.0279 0.7315
9.000 0.7851 0.01638 0.00974 0.0245 0.0234 0.7356
9.250 0.7982 0.01703 0.01044 0.0259 0.0212 0.7400
9.500 0.8102 0.01779 0.01121 0.0274 0.0193 0.7442
9.750 0.8195 0.01867 0.01214 0.0291 0.0173 0.7492
10.000 0.8337 0.01933 0.01286 0.0303 0.0162 0.7542
10.250 0.8463 0.02012 0.01367 0.0315 0.0148 0.7592
10.500 0.8525 0.02125 0.01487 0.0333 0.0133 0.7648
10.750 0.8667 0.02196 0.01564 0.0343 0.0128 0.7711
11.000 0.8797 0.02275 0.01649 0.0353 0.0119 0.7776
11.250 0.8901 0.02370 0.01751 0.0365 0.0115 0.7851
11.500 0.8988 0.02478 0.01863 0.0378 0.0105 0.7930
11.750 0.9027 0.02618 0.02014 0.0395 0.0100 0.8026
12.000 0.9172 0.02689 0.02094 0.0403 0.0095 0.8131
12.250 0.9256 0.02799 0.02215 0.0415 0.0093 0.8264
12.500 0.9333 0.02911 0.02339 0.0429 0.0090 0.8443
12.750 0.9409 0.03012 0.02456 0.0443 0.0088 0.8726
13.000 0.9657 0.03129 0.02601 0.0420 0.0083 0.9420
13.250 0.9887 0.03390 0.02873 0.0376 0.0075 1.0000
13.500 0.9927 0.03572 0.03061 0.0385 0.0074 1.0000
13.750 0.9994 0.03735 0.03229 0.0391 0.0074 1.0000
14.000 1.0094 0.03876 0.03376 0.0394 0.0072 1.0000
14.250 1.0208 0.04010 0.03515 0.0397 0.0070 1.0000
14.500 1.0308 0.04157 0.03668 0.0399 0.0067 1.0000
14.750 1.0311 0.04391 0.03910 0.0405 0.0068 1.0000
15.000 1.0390 0.04566 0.04090 0.0407 0.0066 1.0000
15.250 1.0432 0.04777 0.04309 0.0409 0.0066 1.0000
15.500 1.0483 0.04986 0.04524 0.0410 0.0065 1.0000
15.750 1.0552 0.05183 0.04726 0.0409 0.0061 1.0000
16.000 1.0605 0.05397 0.04946 0.0408 0.0061 1.0000
16.250 1.0610 0.05668 0.05226 0.0407 0.0060 1.0000
16.500 1.0641 0.05920 0.05485 0.0403 0.0060 1.0000
16.750 1.0695 0.06154 0.05723 0.0398 0.0057 1.0000
17.000 1.0681 0.06463 0.06041 0.0393 0.0057 1.0000
17.250 1.0589 0.06874 0.06462 0.0386 0.0054 1.0000
17.500 1.0616 0.07159 0.06755 0.0379 0.0055 1.0000
17.750 1.0385 0.07760 0.07376 0.0368 0.0052 1.0000
18.000 1.0353 0.08142 0.07768 0.0355 0.0052 1.0000
18.250 1.0309 0.08551 0.08186 0.0341 0.0052 1.0000
18.500 1.0262 0.08976 0.08623 0.0324 0.0052 1.0000
18.750 1.0168 0.09482 0.09141 0.0303 0.0052 1.0000
19.000 1.0131 0.09923 0.09592 0.0282 0.0052 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER E838 HYDROFOIL AIRFOIL (e838-il)