E178 (8.69%) (e178-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: E178 (8.69%) (e178-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.84 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e178-il-1000000-n5.txt Download as CSV file: xf-e178-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E178 (8.69%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5227 0.14120 0.13957 0.0140 1.0000 0.0023
-12.000 -0.5182 0.13682 0.13519 0.0121 1.0000 0.0023
-9.500 -0.7636 0.02596 0.02319 -0.0455 0.8887 0.0029
-9.250 -0.7526 0.02231 0.01899 -0.0447 0.8628 0.0030
-9.000 -0.7347 0.02012 0.01639 -0.0440 0.8423 0.0031
-8.750 -0.7136 0.01859 0.01454 -0.0435 0.8244 0.0033
-8.500 -0.6911 0.01733 0.01299 -0.0431 0.8081 0.0034
-8.250 -0.6673 0.01632 0.01175 -0.0427 0.7936 0.0035
-8.000 -0.6426 0.01551 0.01074 -0.0424 0.7803 0.0036
-7.750 -0.6187 0.01435 0.00933 -0.0421 0.7682 0.0041
-7.500 -0.5922 0.01402 0.00892 -0.0419 0.7571 0.0046
-7.250 -0.5651 0.01393 0.00879 -0.0419 0.7465 0.0051
-6.750 -0.5111 0.01348 0.00820 -0.0417 0.7267 0.0061
-6.500 -0.4843 0.01315 0.00777 -0.0416 0.7182 0.0066
-6.250 -0.4574 0.01281 0.00732 -0.0415 0.7096 0.0069
-6.000 -0.4301 0.01260 0.00704 -0.0414 0.7018 0.0070
-5.500 -0.3774 0.01141 0.00562 -0.0410 0.6876 0.0084
-5.250 -0.3499 0.01124 0.00539 -0.0410 0.6807 0.0090
-5.000 -0.3224 0.01101 0.00512 -0.0410 0.6741 0.0097
-4.500 -0.2679 0.01032 0.00425 -0.0407 0.6618 0.0110
-4.250 -0.2405 0.01003 0.00389 -0.0406 0.6557 0.0117
-4.000 -0.2127 0.00985 0.00364 -0.0406 0.6503 0.0123
-3.750 -0.1850 0.00967 0.00341 -0.0405 0.6445 0.0126
-3.500 -0.1573 0.00946 0.00315 -0.0405 0.6392 0.0129
-3.250 -0.1302 0.00896 0.00253 -0.0403 0.6340 0.0139
-3.000 -0.1025 0.00870 0.00220 -0.0402 0.6286 0.0146
-2.750 -0.0746 0.00851 0.00195 -0.0401 0.6238 0.0151
-2.500 -0.0466 0.00834 0.00172 -0.0401 0.6186 0.0155
-2.250 -0.0187 0.00821 0.00154 -0.0401 0.6134 0.0161
-2.000 0.0094 0.00808 0.00138 -0.0401 0.6088 0.0169
-1.750 0.0375 0.00797 0.00124 -0.0401 0.6038 0.0174
-1.250 0.0938 0.00781 0.00101 -0.0401 0.5941 0.0204
-1.000 0.1217 0.00761 0.00092 -0.0401 0.5891 0.0527
-0.750 0.1493 0.00741 0.00085 -0.0401 0.5844 0.0976
-0.500 0.1773 0.00726 0.00080 -0.0401 0.5794 0.1357
-0.250 0.2051 0.00712 0.00076 -0.0402 0.5744 0.1770
0.000 0.2328 0.00694 0.00073 -0.0402 0.5696 0.2342
0.250 0.2599 0.00661 0.00072 -0.0403 0.5643 0.3425
0.500 0.2856 0.00606 0.00074 -0.0402 0.5590 0.5369
0.750 0.3107 0.00560 0.00077 -0.0397 0.5537 0.6999
1.000 0.3349 0.00528 0.00080 -0.0389 0.5464 0.8184
1.250 0.3594 0.00503 0.00085 -0.0378 0.5381 0.9321
1.500 0.4027 0.00505 0.00087 -0.0411 0.5288 0.9833
1.750 0.4412 0.00511 0.00088 -0.0435 0.5190 0.9975
2.000 0.4712 0.00518 0.00091 -0.0440 0.5086 1.0000
2.250 0.4980 0.00526 0.00096 -0.0438 0.4987 1.0000
2.500 0.5248 0.00536 0.00101 -0.0435 0.4874 1.0000
2.750 0.5516 0.00547 0.00106 -0.0433 0.4745 1.0000
3.000 0.5784 0.00558 0.00113 -0.0432 0.4618 1.0000
3.250 0.6053 0.00570 0.00122 -0.0430 0.4472 1.0000
3.500 0.6320 0.00585 0.00132 -0.0428 0.4289 1.0000
3.750 0.6585 0.00605 0.00143 -0.0426 0.4037 1.0000
4.000 0.6846 0.00632 0.00158 -0.0424 0.3717 1.0000
4.250 0.7102 0.00669 0.00177 -0.0422 0.3292 1.0000
4.500 0.7352 0.00715 0.00205 -0.0419 0.2806 1.0000
4.750 0.7608 0.00752 0.00228 -0.0417 0.2476 1.0000
5.000 0.7849 0.00811 0.00262 -0.0414 0.1925 1.0000
5.250 0.8084 0.00879 0.00301 -0.0410 0.1324 1.0000
5.500 0.8323 0.00938 0.00338 -0.0406 0.0896 1.0000
5.750 0.8564 0.00992 0.00375 -0.0403 0.0572 1.0000
6.000 0.8811 0.01036 0.00412 -0.0399 0.0392 1.0000
6.250 0.9056 0.01081 0.00449 -0.0396 0.0226 1.0000
6.500 0.9291 0.01140 0.00498 -0.0391 0.0074 1.0000
6.750 0.9540 0.01178 0.00537 -0.0387 0.0052 1.0000
7.000 0.9785 0.01220 0.00582 -0.0383 0.0039 1.0000
7.250 1.0027 0.01264 0.00633 -0.0379 0.0032 1.0000
7.500 1.0271 0.01302 0.00675 -0.0375 0.0031 1.0000
7.750 1.0510 0.01347 0.00724 -0.0370 0.0029 1.0000
8.000 1.0743 0.01395 0.00781 -0.0365 0.0028 1.0000
8.250 1.0972 0.01446 0.00838 -0.0359 0.0026 1.0000
8.500 1.1196 0.01501 0.00899 -0.0353 0.0024 1.0000
8.750 1.1413 0.01561 0.00966 -0.0346 0.0023 1.0000
9.000 1.1626 0.01623 0.01034 -0.0339 0.0021 1.0000
9.250 1.1830 0.01690 0.01107 -0.0330 0.0019 1.0000
9.500 1.2021 0.01767 0.01190 -0.0320 0.0018 1.0000
9.750 1.2184 0.01867 0.01301 -0.0307 0.0017 1.0000
10.000 1.2303 0.02001 0.01451 -0.0288 0.0016 1.0000
10.250 1.2392 0.02151 0.01617 -0.0266 0.0015 1.0000
10.500 1.2454 0.02303 0.01784 -0.0241 0.0015 1.0000
10.750 1.2521 0.02409 0.01900 -0.0215 0.0014 1.0000
11.000 1.2563 0.02537 0.02039 -0.0190 0.0014 1.0000
11.250 1.2607 0.02680 0.02194 -0.0168 0.0014 1.0000
11.500 1.2642 0.02843 0.02369 -0.0151 0.0014 1.0000
11.750 1.2670 0.03027 0.02566 -0.0136 0.0014 1.0000
12.000 1.2679 0.03241 0.02795 -0.0123 0.0014 1.0000
12.250 1.2702 0.03452 0.03019 -0.0113 0.0014 1.0000
12.500 1.2695 0.03706 0.03287 -0.0106 0.0014 1.0000
12.750 1.2667 0.03993 0.03590 -0.0101 0.0014 1.0000
13.000 1.2625 0.04312 0.03926 -0.0099 0.0014 1.0000
13.250 1.2569 0.04659 0.04288 -0.0100 0.0014 1.0000
13.500 1.2499 0.05039 0.04684 -0.0105 0.0014 1.0000
13.750 1.2410 0.05463 0.05124 -0.0115 0.0014 1.0000
14.000 1.2284 0.05961 0.05639 -0.0129 0.0014 1.0000
14.250 1.2165 0.06474 0.06168 -0.0147 0.0014 1.0000
14.500 1.2033 0.07047 0.06758 -0.0172 0.0014 1.0000
14.750 1.1888 0.07685 0.07412 -0.0202 0.0014 1.0000
15.000 1.1725 0.08402 0.08143 -0.0240 0.0014 1.0000
15.250 1.1546 0.09203 0.08959 -0.0284 0.0014 1.0000
15.500 1.1388 0.10019 0.09789 -0.0330 0.0014 1.0000
15.750 1.1201 0.10950 0.10734 -0.0384 0.0014 1.0000
16.000 1.1001 0.11965 0.11761 -0.0443 0.0014 1.0000
16.250 1.0791 0.13058 0.12867 -0.0505 0.0014 1.0000
16.500 1.0576 0.14214 0.14034 -0.0569 0.0014 1.0000
16.750 1.0325 0.15541 0.15372 -0.0641 0.0014 1.0000
17.000 1.0008 0.17188 0.17029 -0.0726 0.0015 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E178 (8.69%) (e178-il)