EPPLER 1213 AIRFOIL (e1213-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER 1213 AIRFOIL (e1213-il) Reynolds number: 200,000 Max Cl/Cd: 51.69 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e1213-il-200000.txt Download as CSV file: xf-e1213-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 1213 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
------ -------- --------- --------- -------- -------- --------
-18.500 -0.8827 0.12598 0.12121 -0.0093 1.0000 0.0433
-18.250 -0.9196 0.11478 0.10974 -0.0165 1.0000 0.0433
-18.000 -0.9373 0.10763 0.10241 -0.0208 1.0000 0.0435
-17.750 -0.9528 0.10103 0.09563 -0.0248 1.0000 0.0439
-17.500 -0.9637 0.09541 0.08985 -0.0281 1.0000 0.0442
-17.250 -0.9716 0.09045 0.08474 -0.0308 1.0000 0.0446
-17.000 -0.9573 0.08955 0.08392 -0.0301 1.0000 0.0455
-16.750 -0.9481 0.08773 0.08215 -0.0304 1.0000 0.0463
-16.500 -0.9452 0.08480 0.07920 -0.0315 1.0000 0.0471
-16.250 -0.9456 0.08136 0.07571 -0.0329 1.0000 0.0481
-16.000 -0.9463 0.07790 0.07218 -0.0344 1.0000 0.0489
-15.750 -0.9481 0.07436 0.06854 -0.0359 1.0000 0.0496
-15.500 -0.9443 0.07203 0.06625 -0.0363 1.0000 0.0509
-15.250 -0.9430 0.06934 0.06359 -0.0371 1.0000 0.0520
-15.000 -0.9465 0.06592 0.06016 -0.0385 1.0000 0.0533
-14.750 -0.9527 0.06209 0.05627 -0.0402 1.0000 0.0547
-14.500 -0.9594 0.05819 0.05229 -0.0418 1.0000 0.0560
-14.250 -0.9680 0.05435 0.04851 -0.0434 1.0000 0.0575
-14.000 -0.9808 0.04971 0.04383 -0.0457 1.0000 0.0592
-13.750 -0.9933 0.04506 0.03909 -0.0481 1.0000 0.0613
-13.500 -1.0066 0.04046 0.03442 -0.0505 1.0000 0.0631
-13.250 -1.0216 0.03598 0.02990 -0.0529 1.0000 0.0652
-13.000 -1.0330 0.03255 0.02636 -0.0538 1.0000 0.0683
-12.750 -1.0470 0.02974 0.02353 -0.0529 1.0000 0.0720
-12.500 -1.0570 0.02774 0.02149 -0.0505 1.0000 0.0781
-12.250 -1.0647 0.02614 0.01991 -0.0470 1.0000 0.0862
-12.000 -1.0642 0.02474 0.01856 -0.0444 1.0000 0.0975
-11.750 -1.0556 0.02373 0.01756 -0.0424 1.0000 0.1095
-11.500 -1.0423 0.02301 0.01682 -0.0407 1.0000 0.1203
-11.250 -1.0263 0.02244 0.01621 -0.0392 1.0000 0.1294
-11.000 -1.0082 0.02199 0.01564 -0.0379 1.0000 0.1381
-10.750 -0.9899 0.02166 0.01535 -0.0365 1.0000 0.1452
-10.500 -0.9708 0.02130 0.01492 -0.0351 1.0000 0.1523
-10.250 -0.9507 0.02111 0.01474 -0.0338 1.0000 0.1587
-10.000 -0.9311 0.02080 0.01433 -0.0325 1.0000 0.1651
-9.750 -0.9104 0.02069 0.01427 -0.0312 1.0000 0.1705
-9.500 -0.8911 0.02047 0.01391 -0.0297 1.0000 0.1766
-9.250 -0.8707 0.02028 0.01380 -0.0284 1.0000 0.1816
-9.000 -0.8510 0.02030 0.01384 -0.0269 1.0000 0.1874
-8.750 -0.8350 0.02014 0.01357 -0.0250 1.0000 0.1932
-8.500 -0.8071 0.02022 0.01382 -0.0253 0.9952 0.1987
-8.250 -0.7590 0.02028 0.01368 -0.0293 0.9767 0.2073
-8.000 -0.7122 0.02016 0.01373 -0.0328 0.9535 0.2139
-7.750 -0.6662 0.02010 0.01353 -0.0360 0.9256 0.2214
-7.500 -0.6260 0.01968 0.01301 -0.0382 0.8947 0.2271
-7.250 -0.5948 0.01961 0.01288 -0.0383 0.8626 0.2316
-7.000 -0.5702 0.01950 0.01258 -0.0372 0.8338 0.2365
-6.750 -0.5472 0.01942 0.01219 -0.0359 0.8092 0.2409
-6.500 -0.5220 0.01895 0.01171 -0.0351 0.7878 0.2451
-6.250 -0.4966 0.01883 0.01151 -0.0342 0.7679 0.2492
-6.000 -0.4715 0.01868 0.01121 -0.0334 0.7494 0.2539
-5.750 -0.4466 0.01856 0.01084 -0.0325 0.7321 0.2583
-5.500 -0.4206 0.01808 0.01033 -0.0320 0.7161 0.2624
-5.250 -0.3942 0.01791 0.01011 -0.0313 0.7010 0.2665
-5.000 -0.3680 0.01777 0.00984 -0.0307 0.6865 0.2712
-4.750 -0.3418 0.01762 0.00951 -0.0301 0.6717 0.2757
-4.500 -0.3152 0.01724 0.00906 -0.0296 0.6584 0.2800
-4.250 -0.2884 0.01706 0.00884 -0.0291 0.6459 0.2843
-4.000 -0.2613 0.01690 0.00863 -0.0287 0.6324 0.2889
-3.750 -0.2345 0.01679 0.00835 -0.0282 0.6206 0.2936
-3.500 -0.2075 0.01650 0.00799 -0.0278 0.6086 0.2982
-3.250 -0.1802 0.01631 0.00781 -0.0274 0.5969 0.3027
-3.000 -0.1530 0.01620 0.00759 -0.0269 0.5862 0.3076
-2.750 -0.1256 0.01609 0.00741 -0.0266 0.5744 0.3127
-2.500 -0.0983 0.01590 0.00712 -0.0262 0.5648 0.3177
-2.250 -0.0709 0.01572 0.00700 -0.0258 0.5534 0.3228
-2.000 -0.0435 0.01566 0.00684 -0.0255 0.5440 0.3284
-1.750 -0.0159 0.01561 0.00670 -0.0251 0.5333 0.3340
-1.500 0.0113 0.01542 0.00652 -0.0247 0.5244 0.3400
-1.250 0.0388 0.01531 0.00644 -0.0244 0.5141 0.3464
-1.000 0.0664 0.01533 0.00631 -0.0240 0.5056 0.3530
-0.750 0.0936 0.01513 0.00622 -0.0237 0.4958 0.3600
-0.500 0.1209 0.01514 0.00613 -0.0233 0.4877 0.3682
-0.250 0.1482 0.01502 0.00608 -0.0230 0.4781 0.3766
0.000 0.1754 0.01496 0.00601 -0.0226 0.4701 0.3857
0.250 0.2025 0.01491 0.00600 -0.0222 0.4614 0.3963
0.500 0.2295 0.01485 0.00596 -0.0218 0.4532 0.4089
0.750 0.2561 0.01481 0.00598 -0.0214 0.4453 0.4230
1.000 0.2828 0.01473 0.00598 -0.0209 0.4369 0.4399
1.250 0.3092 0.01474 0.00599 -0.0204 0.4299 0.4608
1.500 0.3351 0.01462 0.00607 -0.0198 0.4216 0.4881
1.750 0.3605 0.01452 0.00610 -0.0191 0.4146 0.5240
2.000 0.3851 0.01445 0.00623 -0.0183 0.4075 0.5726
2.250 0.4087 0.01427 0.00634 -0.0171 0.4001 0.6360
2.500 0.4316 0.01417 0.00645 -0.0157 0.3939 0.7137
2.750 0.4559 0.01401 0.00670 -0.0142 0.3868 0.8066
3.000 0.5047 0.01407 0.00691 -0.0175 0.3786 0.9039
3.250 0.5612 0.01435 0.00716 -0.0228 0.3697 0.9554
3.500 0.6107 0.01455 0.00728 -0.0268 0.3614 0.9833
3.750 0.6651 0.01483 0.00746 -0.0321 0.3536 1.0000
4.000 0.6860 0.01501 0.00762 -0.0308 0.3475 1.0000
4.250 0.7079 0.01522 0.00773 -0.0297 0.3421 1.0000
4.500 0.7299 0.01553 0.00797 -0.0286 0.3366 1.0000
4.750 0.7519 0.01574 0.00820 -0.0275 0.3305 1.0000
5.000 0.7746 0.01598 0.00835 -0.0264 0.3252 1.0000
5.250 0.7978 0.01637 0.00864 -0.0255 0.3203 1.0000
5.500 0.8198 0.01663 0.00896 -0.0244 0.3149 1.0000
5.750 0.8428 0.01689 0.00919 -0.0235 0.3097 1.0000
6.000 0.8665 0.01727 0.00943 -0.0226 0.3051 1.0000
6.250 0.8883 0.01761 0.00985 -0.0215 0.3000 1.0000
6.500 0.9107 0.01791 0.01016 -0.0205 0.2949 1.0000
6.750 0.9340 0.01823 0.01041 -0.0197 0.2905 1.0000
7.000 0.9579 0.01875 0.01084 -0.0190 0.2864 1.0000
7.250 0.9791 0.01911 0.01132 -0.0178 0.2820 1.0000
7.500 1.0016 0.01947 0.01169 -0.0169 0.2775 1.0000
7.750 1.0251 0.01983 0.01199 -0.0161 0.2736 1.0000
8.000 1.0492 0.02041 0.01249 -0.0155 0.2697 1.0000
8.250 1.0693 0.02083 0.01305 -0.0143 0.2657 1.0000
8.500 1.0911 0.02127 0.01354 -0.0134 0.2619 1.0000
8.750 1.1142 0.02169 0.01394 -0.0126 0.2584 1.0000
9.000 1.1387 0.02224 0.01440 -0.0122 0.2553 1.0000
9.250 1.1595 0.02289 0.01513 -0.0112 0.2520 1.0000
9.500 1.1783 0.02342 0.01578 -0.0100 0.2485 1.0000
9.750 1.1990 0.02391 0.01632 -0.0090 0.2451 1.0000
10.000 1.2214 0.02440 0.01680 -0.0083 0.2422 1.0000
10.250 1.2459 0.02501 0.01734 -0.0079 0.2395 1.0000
10.500 1.2659 0.02584 0.01823 -0.0070 0.2367 1.0000
10.750 1.2806 0.02652 0.01909 -0.0054 0.2338 1.0000
11.000 1.2974 0.02717 0.01984 -0.0041 0.2308 1.0000
11.250 1.3165 0.02776 0.02047 -0.0030 0.2280 1.0000
11.500 1.3386 0.02830 0.02098 -0.0024 0.2255 1.0000
11.750 1.3650 0.02914 0.02172 -0.0025 0.2227 1.0000
12.000 1.3742 0.03005 0.02283 -0.0004 0.2205 1.0000
12.250 1.3812 0.03097 0.02393 0.0019 0.2179 1.0000
12.500 1.3906 0.03183 0.02490 0.0038 0.2154 1.0000
12.750 1.4024 0.03251 0.02562 0.0056 0.2129 1.0000
13.000 1.4210 0.03304 0.02613 0.0066 0.2105 1.0000
13.250 1.4521 0.03382 0.02680 0.0058 0.2077 1.0000
13.500 1.4466 0.03506 0.02823 0.0093 0.2058 1.0000
13.750 1.4362 0.03653 0.02990 0.0126 0.2039 1.0000
14.000 1.4274 0.03823 0.03176 0.0149 0.2017 1.0000
14.250 1.4255 0.03980 0.03345 0.0163 0.1994 1.0000
14.500 1.4352 0.04084 0.03451 0.0172 0.1970 1.0000
14.750 1.4637 0.04094 0.03451 0.0174 0.1944 1.0000
15.000 1.4752 0.04240 0.03600 0.0180 0.1920 1.0000
15.250 1.4452 0.04598 0.03985 0.0191 0.1903 1.0000
15.500 1.4101 0.05078 0.04491 0.0190 0.1882 1.0000
15.750 1.3693 0.05693 0.05129 0.0175 0.1859 1.0000
16.000 1.3304 0.06366 0.05820 0.0152 0.1834 1.0000
16.250 1.4002 0.05853 0.05287 0.0179 0.1810 1.0000
16.500 1.4474 0.05660 0.05079 0.0194 0.1782 1.0000
16.750 0.5931 0.17184 0.16779 -0.0430 0.1539 1.0000
17.000 0.6259 0.17300 0.16896 -0.0413 0.1524 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER 1213 AIRFOIL (e1213-il)