EPPLER 715 AIRFOIL (e715-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: EPPLER 715 AIRFOIL (e715-il) Reynolds number: 500,000 Max Cl/Cd: 98 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e715-il-500000-n5.txt Download as CSV file: xf-e715-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 715 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.7405 0.12272 0.12003 -0.0008 1.0000 0.0044
-16.000 -0.7688 0.11173 0.10887 -0.0069 1.0000 0.0042
-15.750 -0.7905 0.10257 0.09958 -0.0121 1.0000 0.0042
-15.500 -0.8130 0.09363 0.09051 -0.0172 1.0000 0.0041
-15.250 -0.8320 0.08562 0.08238 -0.0220 1.0000 0.0042
-15.000 -0.8480 0.07852 0.07514 -0.0262 1.0000 0.0041
-14.750 -0.8624 0.07189 0.06840 -0.0302 1.0000 0.0042
-14.500 -0.8750 0.06604 0.06243 -0.0337 1.0000 0.0043
-14.250 -0.8895 0.06039 0.05665 -0.0370 1.0000 0.0041
-14.000 -0.8874 0.05478 0.05055 -0.0437 0.8215 0.0043
-13.750 -0.8967 0.05102 0.04652 -0.0451 0.7769 0.0043
-13.500 -0.9079 0.04694 0.04223 -0.0468 0.7517 0.0042
-13.250 -0.9119 0.04375 0.03887 -0.0481 0.7316 0.0044
-13.000 -0.9188 0.04032 0.03525 -0.0494 0.7156 0.0043
-12.750 -0.9204 0.03749 0.03227 -0.0504 0.7021 0.0044
-12.500 -0.9245 0.03441 0.02903 -0.0516 0.6903 0.0044
-12.250 -0.9257 0.03170 0.02616 -0.0527 0.6794 0.0044
-12.000 -0.9285 0.02932 0.02363 -0.0531 0.6699 0.0045
-11.750 -0.9304 0.02775 0.02191 -0.0514 0.6611 0.0045
-11.500 -0.9234 0.02649 0.02051 -0.0501 0.6529 0.0046
-11.250 -0.9117 0.02533 0.01920 -0.0491 0.6454 0.0048
-11.000 -0.8976 0.02424 0.01797 -0.0483 0.6384 0.0049
-10.750 -0.8815 0.02325 0.01684 -0.0475 0.6320 0.0051
-10.500 -0.8633 0.02236 0.01581 -0.0468 0.6266 0.0052
-10.250 -0.8442 0.02148 0.01482 -0.0462 0.6211 0.0054
-10.000 -0.8251 0.02055 0.01377 -0.0455 0.6162 0.0056
-9.750 -0.8039 0.01980 0.01293 -0.0450 0.6118 0.0059
-9.500 -0.7815 0.01914 0.01218 -0.0446 0.6072 0.0061
-9.250 -0.7587 0.01851 0.01145 -0.0442 0.6027 0.0065
-9.000 -0.7352 0.01793 0.01075 -0.0438 0.5986 0.0069
-8.750 -0.7111 0.01738 0.01010 -0.0435 0.5947 0.0073
-8.500 -0.6872 0.01677 0.00944 -0.0432 0.5908 0.0080
-8.250 -0.6624 0.01630 0.00889 -0.0429 0.5873 0.0089
-8.000 -0.6373 0.01584 0.00835 -0.0426 0.5842 0.0102
-7.750 -0.6120 0.01537 0.00783 -0.0424 0.5813 0.0118
-7.500 -0.5863 0.01493 0.00735 -0.0422 0.5784 0.0136
-7.250 -0.5602 0.01454 0.00691 -0.0420 0.5754 0.0160
-7.000 -0.5342 0.01414 0.00647 -0.0418 0.5725 0.0190
-6.750 -0.5079 0.01379 0.00608 -0.0417 0.5697 0.0227
-6.500 -0.4814 0.01344 0.00570 -0.0416 0.5671 0.0282
-6.250 -0.4548 0.01307 0.00535 -0.0415 0.5645 0.0353
-6.000 -0.4280 0.01272 0.00502 -0.0414 0.5620 0.0448
-5.750 -0.4012 0.01238 0.00470 -0.0413 0.5596 0.0567
-5.500 -0.3742 0.01205 0.00439 -0.0413 0.5573 0.0715
-5.250 -0.3473 0.01172 0.00410 -0.0412 0.5552 0.0896
-5.000 -0.3202 0.01142 0.00384 -0.0412 0.5530 0.1107
-4.750 -0.2931 0.01108 0.00358 -0.0412 0.5509 0.1382
-4.500 -0.2659 0.01073 0.00334 -0.0412 0.5486 0.1696
-4.250 -0.2385 0.01040 0.00312 -0.0412 0.5464 0.2023
-4.000 -0.2110 0.01012 0.00292 -0.0412 0.5443 0.2354
-3.750 -0.1835 0.00983 0.00273 -0.0412 0.5424 0.2728
-3.500 -0.1562 0.00955 0.00257 -0.0413 0.5404 0.3165
-3.250 -0.1284 0.00936 0.00247 -0.0413 0.5385 0.3540
-3.000 -0.1003 0.00925 0.00242 -0.0413 0.5365 0.3832
-2.750 -0.0716 0.00919 0.00239 -0.0414 0.5346 0.4043
-2.500 -0.0427 0.00916 0.00237 -0.0414 0.5327 0.4210
-2.250 -0.0138 0.00915 0.00236 -0.0415 0.5308 0.4336
-2.000 0.0151 0.00916 0.00234 -0.0416 0.5289 0.4440
-1.750 0.0442 0.00918 0.00232 -0.0418 0.5269 0.4529
-1.500 0.0730 0.00920 0.00231 -0.0418 0.5250 0.4596
-1.250 0.1020 0.00923 0.00230 -0.0420 0.5231 0.4661
-1.000 0.1309 0.00927 0.00229 -0.0421 0.5215 0.4719
-0.750 0.1599 0.00928 0.00231 -0.0422 0.5199 0.4776
-0.500 0.1890 0.00930 0.00232 -0.0424 0.5180 0.4832
-0.250 0.2181 0.00931 0.00232 -0.0425 0.5159 0.4873
0.000 0.2470 0.00932 0.00233 -0.0426 0.5139 0.4913
0.250 0.2759 0.00934 0.00235 -0.0428 0.5120 0.4956
0.500 0.3049 0.00939 0.00236 -0.0429 0.5103 0.5001
0.750 0.3337 0.00941 0.00238 -0.0430 0.5085 0.5037
1.000 0.3623 0.00946 0.00241 -0.0432 0.5066 0.5072
1.250 0.3913 0.00947 0.00246 -0.0433 0.5048 0.5105
1.500 0.4203 0.00950 0.00250 -0.0435 0.5029 0.5138
1.750 0.4493 0.00954 0.00254 -0.0437 0.5007 0.5167
2.000 0.4780 0.00954 0.00259 -0.0438 0.4985 0.5195
2.250 0.5067 0.00956 0.00264 -0.0439 0.4964 0.5224
2.500 0.5354 0.00960 0.00268 -0.0441 0.4943 0.5253
2.750 0.5640 0.00966 0.00274 -0.0442 0.4921 0.5285
3.000 0.5927 0.00971 0.00281 -0.0444 0.4897 0.5315
3.250 0.6214 0.00972 0.00289 -0.0445 0.4867 0.5341
3.500 0.6499 0.00973 0.00296 -0.0446 0.4833 0.5372
3.750 0.6784 0.00976 0.00302 -0.0447 0.4800 0.5406
4.000 0.7067 0.00982 0.00307 -0.0448 0.4768 0.5440
4.250 0.7353 0.00985 0.00317 -0.0450 0.4730 0.5471
4.500 0.7637 0.00987 0.00326 -0.0451 0.4686 0.5505
4.750 0.7918 0.00990 0.00334 -0.0452 0.4643 0.5544
5.000 0.8199 0.00995 0.00343 -0.0453 0.4598 0.5587
5.250 0.8482 0.00999 0.00354 -0.0454 0.4544 0.5627
5.500 0.8760 0.01004 0.00364 -0.0454 0.4489 0.5670
5.750 0.9039 0.01009 0.00377 -0.0455 0.4430 0.5723
6.000 0.9316 0.01015 0.00389 -0.0455 0.4353 0.5784
6.250 0.9590 0.01022 0.00403 -0.0455 0.4262 0.5852
6.500 0.9860 0.01032 0.00417 -0.0454 0.4159 0.5931
6.750 1.0125 0.01044 0.00434 -0.0453 0.4030 0.6024
7.000 1.0385 0.01061 0.00454 -0.0452 0.3871 0.6145
7.250 1.0633 0.01085 0.00481 -0.0449 0.3657 0.6326
7.500 1.0858 0.01121 0.00517 -0.0443 0.3374 0.6633
7.750 1.1041 0.01150 0.00565 -0.0430 0.3067 0.7652
8.000 1.1366 0.01199 0.00635 -0.0448 0.2677 1.0000
8.250 1.1552 0.01278 0.00699 -0.0439 0.2365 1.0000
8.500 1.1732 0.01355 0.00764 -0.0428 0.2102 1.0000
8.750 1.1902 0.01435 0.00832 -0.0417 0.1857 1.0000
9.000 1.2060 0.01515 0.00903 -0.0404 0.1631 1.0000
9.250 1.2194 0.01603 0.00982 -0.0389 0.1429 1.0000
9.500 1.2319 0.01688 0.01060 -0.0372 0.1263 1.0000
9.750 1.2415 0.01776 0.01144 -0.0352 0.1126 1.0000
10.000 1.2435 0.01877 0.01242 -0.0322 0.1014 1.0000
10.250 1.2455 0.02002 0.01367 -0.0299 0.0921 1.0000
10.500 1.2488 0.02154 0.01520 -0.0285 0.0842 1.0000
10.750 1.2514 0.02335 0.01701 -0.0274 0.0757 1.0000
11.000 1.2549 0.02522 0.01888 -0.0266 0.0677 1.0000
11.250 1.2595 0.02706 0.02073 -0.0259 0.0616 1.0000
11.500 1.2620 0.02910 0.02277 -0.0252 0.0552 1.0000
11.750 1.2668 0.03097 0.02466 -0.0246 0.0502 1.0000
12.000 1.2685 0.03312 0.02681 -0.0240 0.0449 1.0000
12.250 1.2733 0.03502 0.02875 -0.0235 0.0411 1.0000
12.500 1.2746 0.03725 0.03098 -0.0229 0.0369 1.0000
12.750 1.2789 0.03923 0.03299 -0.0225 0.0336 1.0000
13.000 1.2807 0.04146 0.03524 -0.0221 0.0302 1.0000
13.250 1.2837 0.04361 0.03743 -0.0217 0.0276 1.0000
13.500 1.2865 0.04580 0.03967 -0.0214 0.0251 1.0000
13.750 1.2888 0.04815 0.04204 -0.0213 0.0233 1.0000
14.000 1.2929 0.05038 0.04433 -0.0212 0.0210 1.0000
14.250 1.2956 0.05283 0.04680 -0.0212 0.0193 1.0000
14.500 1.2989 0.05526 0.04929 -0.0212 0.0179 1.0000
14.750 1.3026 0.05769 0.05177 -0.0213 0.0165 1.0000
15.000 1.3043 0.06040 0.05452 -0.0215 0.0149 1.0000
15.250 1.3071 0.06302 0.05720 -0.0218 0.0140 1.0000
15.500 1.3097 0.06574 0.05999 -0.0222 0.0128 1.0000
15.750 1.3118 0.06855 0.06287 -0.0226 0.0120 1.0000
16.000 1.3124 0.07164 0.06601 -0.0231 0.0113 1.0000
16.250 1.3148 0.07450 0.06894 -0.0236 0.0105 1.0000
16.500 1.3156 0.07767 0.07219 -0.0243 0.0097 1.0000
16.750 1.3154 0.08100 0.07557 -0.0251 0.0089 1.0000
17.250 1.3148 0.08789 0.08262 -0.0270 0.0078 1.0000
17.500 1.3146 0.09142 0.08624 -0.0281 0.0075 1.0000
17.750 1.3128 0.09525 0.09016 -0.0293 0.0072 1.0000
18.000 1.3101 0.09926 0.09426 -0.0307 0.0067 1.0000
18.250 1.3066 0.10346 0.09852 -0.0322 0.0063 1.0000
18.500 1.3037 0.10765 0.10282 -0.0338 0.0060 1.0000
18.750 1.3009 0.11189 0.10717 -0.0355 0.0056 1.0000
19.000 1.2975 0.11629 0.11166 -0.0374 0.0053 1.0000
19.250 1.2929 0.12096 0.11642 -0.0395 0.0051 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EPPLER 715 AIRFOIL (e715-il)