EPPLER 748 AIRFOIL (e748-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 748 AIRFOIL (e748-il) Reynolds number: 500,000 Max Cl/Cd: 93.4 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e748-il-500000-n5.txt Download as CSV file: xf-e748-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 748 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
------ -------- --------- --------- -------- -------- --------
-19.500 -0.6554 0.14277 0.13939 -0.0436 1.0000 0.0127
-19.250 -0.6706 0.13589 0.13239 -0.0470 1.0000 0.0128
-19.000 -0.6836 0.12971 0.12610 -0.0500 1.0000 0.0128
-18.750 -0.6926 0.12442 0.12072 -0.0524 1.0000 0.0128
-18.500 -0.7015 0.11926 0.11547 -0.0548 1.0000 0.0129
-18.250 -0.7080 0.11460 0.11073 -0.0568 1.0000 0.0129
-18.000 -0.7151 0.11001 0.10606 -0.0588 1.0000 0.0130
-17.750 -0.7204 0.10575 0.10171 -0.0606 1.0000 0.0131
-17.500 -0.7251 0.10167 0.09755 -0.0622 1.0000 0.0131
-17.250 -0.7288 0.09786 0.09368 -0.0637 1.0000 0.0132
-17.000 -0.7321 0.09419 0.08993 -0.0650 1.0000 0.0132
-16.750 -0.7357 0.09053 0.08620 -0.0664 1.0000 0.0133
-16.500 -0.7373 0.08726 0.08287 -0.0674 1.0000 0.0134
-16.250 -0.7394 0.08401 0.07957 -0.0684 1.0000 0.0134
-16.000 -0.7403 0.08096 0.07645 -0.0692 1.0000 0.0135
-15.750 -0.7412 0.07800 0.07344 -0.0700 1.0000 0.0135
-15.500 -0.7416 0.07515 0.07053 -0.0707 1.0000 0.0136
-15.250 -0.7423 0.07236 0.06768 -0.0712 1.0000 0.0137
-15.000 -0.7423 0.06980 0.06509 -0.0716 1.0000 0.0137
-14.750 -0.7438 0.06716 0.06242 -0.0719 1.0000 0.0138
-14.500 -0.7378 0.06424 0.05947 -0.0739 0.9993 0.0140
-14.250 -0.7256 0.06122 0.05640 -0.0773 0.9977 0.0141
-14.000 -0.7136 0.05832 0.05346 -0.0804 0.9960 0.0143
-13.750 -0.7012 0.05554 0.05064 -0.0835 0.9943 0.0145
-13.500 -0.6869 0.05292 0.04797 -0.0867 0.9927 0.0146
-13.250 -0.6753 0.05055 0.04556 -0.0888 0.9903 0.0148
-13.000 -0.6611 0.04816 0.04313 -0.0915 0.9875 0.0150
-12.750 -0.6458 0.04578 0.04071 -0.0944 0.9850 0.0153
-12.500 -0.6278 0.04354 0.03842 -0.0978 0.9829 0.0156
-12.250 -0.6167 0.04144 0.03628 -0.0995 0.9791 0.0158
-12.000 -0.6057 0.03940 0.03420 -0.1012 0.9741 0.0160
-11.500 -0.5876 0.03540 0.03011 -0.1037 0.9608 0.0164
-11.250 -0.5874 0.03366 0.02833 -0.1028 0.9477 0.0165
-10.750 -0.5756 0.02950 0.02408 -0.1043 0.9139 0.0170
-10.500 -0.5439 0.02691 0.02142 -0.1104 0.8990 0.0175
-10.250 -0.4803 0.02446 0.01885 -0.1220 0.8833 0.0182
-10.000 -0.4227 0.02244 0.01663 -0.1321 0.8547 0.0191
-9.750 -0.3990 0.02088 0.01485 -0.1353 0.8194 0.0197
-9.500 -0.3843 0.01939 0.01315 -0.1369 0.7892 0.0202
-9.250 -0.3673 0.01789 0.01147 -0.1389 0.7644 0.0210
-9.000 -0.3480 0.01708 0.01052 -0.1393 0.7437 0.0222
-8.500 -0.3047 0.01584 0.00906 -0.1398 0.7101 0.0261
-8.250 -0.2815 0.01529 0.00844 -0.1401 0.6953 0.0303
-8.000 -0.2575 0.01478 0.00787 -0.1404 0.6810 0.0371
-7.750 -0.2325 0.01428 0.00733 -0.1407 0.6667 0.0466
-7.250 -0.1803 0.01344 0.00643 -0.1414 0.6426 0.0670
-7.000 -0.1532 0.01305 0.00602 -0.1419 0.6313 0.0797
-6.750 -0.1259 0.01269 0.00565 -0.1423 0.6205 0.0944
-6.500 -0.0983 0.01228 0.00525 -0.1428 0.6094 0.1140
-6.250 -0.0699 0.01182 0.00485 -0.1436 0.5996 0.1410
-6.000 -0.0413 0.01126 0.00438 -0.1445 0.5903 0.1834
-5.750 -0.0116 0.01058 0.00389 -0.1458 0.5817 0.2423
-5.500 0.0177 0.01022 0.00369 -0.1466 0.5726 0.3002
-5.250 0.0467 0.01020 0.00368 -0.1468 0.5641 0.3271
-5.000 0.0754 0.01025 0.00366 -0.1469 0.5556 0.3413
-4.750 0.1042 0.01032 0.00368 -0.1470 0.5488 0.3513
-4.500 0.1331 0.01037 0.00364 -0.1471 0.5413 0.3582
-4.250 0.1614 0.01046 0.00369 -0.1470 0.5341 0.3641
-4.000 0.1904 0.01052 0.00368 -0.1472 0.5271 0.3694
-3.750 0.2191 0.01061 0.00364 -0.1472 0.5201 0.3736
-3.500 0.2475 0.01067 0.00369 -0.1472 0.5145 0.3783
-3.250 0.2764 0.01076 0.00375 -0.1473 0.5086 0.3829
-3.000 0.3048 0.01084 0.00376 -0.1473 0.5025 0.3864
-2.750 0.3332 0.01091 0.00374 -0.1473 0.4968 0.3889
-2.500 0.3621 0.01094 0.00370 -0.1474 0.4912 0.3906
-2.250 0.3906 0.01097 0.00367 -0.1475 0.4858 0.3920
-1.750 0.4473 0.01100 0.00363 -0.1475 0.4765 0.3948
-1.500 0.4758 0.01103 0.00364 -0.1476 0.4713 0.3963
-1.250 0.5038 0.01109 0.00365 -0.1476 0.4662 0.3978
-1.000 0.5318 0.01115 0.00367 -0.1475 0.4618 0.3991
-0.750 0.5605 0.01118 0.00368 -0.1476 0.4579 0.4003
-0.500 0.5888 0.01123 0.00370 -0.1477 0.4537 0.4017
-0.250 0.6167 0.01129 0.00372 -0.1476 0.4493 0.4030
0.000 0.6442 0.01139 0.00376 -0.1475 0.4450 0.4043
0.250 0.6727 0.01143 0.00379 -0.1476 0.4413 0.4058
0.500 0.7008 0.01149 0.00383 -0.1476 0.4372 0.4073
0.750 0.7285 0.01157 0.00388 -0.1475 0.4334 0.4085
1.000 0.7559 0.01167 0.00394 -0.1474 0.4297 0.4094
1.250 0.7835 0.01173 0.00399 -0.1474 0.4263 0.4109
1.500 0.8115 0.01178 0.00406 -0.1474 0.4227 0.4123
1.750 0.8390 0.01185 0.00414 -0.1473 0.4187 0.4137
2.000 0.8662 0.01194 0.00422 -0.1471 0.4149 0.4151
2.250 0.8929 0.01206 0.00432 -0.1469 0.4115 0.4165
2.500 0.9201 0.01216 0.00442 -0.1468 0.4086 0.4181
2.750 0.9476 0.01224 0.00452 -0.1467 0.4053 0.4196
3.000 0.9745 0.01234 0.00463 -0.1465 0.4015 0.4214
3.250 1.0009 0.01246 0.00474 -0.1463 0.3978 0.4232
3.500 1.0268 0.01261 0.00487 -0.1459 0.3944 0.4249
3.750 1.0532 0.01274 0.00500 -0.1457 0.3915 0.4264
4.000 1.0799 0.01284 0.00512 -0.1455 0.3882 0.4276
4.250 1.1062 0.01294 0.00526 -0.1452 0.3846 0.4294
4.500 1.1317 0.01307 0.00541 -0.1448 0.3810 0.4312
4.750 1.1566 0.01323 0.00557 -0.1443 0.3777 0.4331
5.000 1.1818 0.01338 0.00574 -0.1439 0.3745 0.4350
5.250 1.2072 0.01349 0.00591 -0.1435 0.3713 0.4370
5.500 1.2317 0.01363 0.00607 -0.1429 0.3679 0.4390
5.750 1.2552 0.01379 0.00625 -0.1421 0.3645 0.4411
6.000 1.2776 0.01399 0.00644 -0.1411 0.3609 0.4433
6.250 1.3007 0.01417 0.00664 -0.1403 0.3578 0.4455
6.500 1.3249 0.01432 0.00685 -0.1397 0.3548 0.4480
6.750 1.3483 0.01450 0.00708 -0.1390 0.3513 0.4506
7.000 1.3708 0.01471 0.00732 -0.1382 0.3476 0.4532
7.250 1.3922 0.01496 0.00759 -0.1371 0.3442 0.4559
7.500 1.4146 0.01519 0.00786 -0.1363 0.3412 0.4588
7.750 1.4375 0.01539 0.00812 -0.1355 0.3377 0.4618
8.000 1.4593 0.01563 0.00840 -0.1346 0.3340 0.4646
8.250 1.4802 0.01590 0.00871 -0.1335 0.3303 0.4678
8.500 1.4993 0.01624 0.00906 -0.1322 0.3266 0.4714
8.750 1.5213 0.01647 0.00938 -0.1313 0.3232 0.4754
9.000 1.5421 0.01675 0.00972 -0.1303 0.3193 0.4797
9.500 1.5789 0.01749 0.01053 -0.1276 0.3112 0.4890
9.750 1.5986 0.01783 0.01095 -0.1265 0.3075 0.4952
10.000 1.6179 0.01818 0.01137 -0.1254 0.3034 0.5017
10.250 1.6349 0.01862 0.01187 -0.1239 0.2989 0.5089
10.500 1.6494 0.01918 0.01245 -0.1222 0.2944 0.5169
10.750 1.6678 0.01959 0.01297 -0.1210 0.2900 0.5259
11.000 1.6837 0.02012 0.01357 -0.1196 0.2848 0.5369
11.250 1.6961 0.02081 0.01431 -0.1177 0.2797 0.5492
11.500 1.7115 0.02140 0.01500 -0.1164 0.2747 0.5647
11.750 1.7249 0.02211 0.01580 -0.1148 0.2689 0.5839
12.000 1.7337 0.02306 0.01682 -0.1128 0.2632 0.6069
12.250 1.7477 0.02380 0.01769 -0.1115 0.2577 0.6377
12.500 1.7568 0.02484 0.01885 -0.1098 0.2511 0.6756
12.750 1.7647 0.02598 0.02013 -0.1081 0.2447 0.7274
13.000 1.7684 0.02701 0.02149 -0.1056 0.2372 0.8792
13.250 1.7681 0.02856 0.02310 -0.1032 0.2298 1.0000
13.500 1.7704 0.03040 0.02495 -0.1015 0.2211 1.0000
13.750 1.7703 0.03253 0.02709 -0.0999 0.2123 1.0000
14.000 1.7662 0.03511 0.02967 -0.0984 0.2036 1.0000
14.250 1.7649 0.03762 0.03220 -0.0972 0.1948 1.0000
14.500 1.7585 0.04070 0.03531 -0.0961 0.1870 1.0000
14.750 1.7550 0.04366 0.03831 -0.0953 0.1792 1.0000
15.000 1.7470 0.04721 0.04189 -0.0946 0.1726 1.0000
15.250 1.7404 0.05074 0.04546 -0.0941 0.1649 1.0000
15.500 1.7296 0.05488 0.04964 -0.0939 0.1581 1.0000
15.750 1.7191 0.05915 0.05395 -0.0939 0.1503 1.0000
16.000 1.7076 0.06368 0.05852 -0.0940 0.1442 1.0000
16.250 1.6971 0.06820 0.06308 -0.0944 0.1374 1.0000
16.500 1.6850 0.07308 0.06801 -0.0950 0.1317 1.0000
16.750 1.6756 0.07768 0.07267 -0.0956 0.1257 1.0000
17.000 1.6620 0.08299 0.07802 -0.0966 0.1199 1.0000
17.250 1.6527 0.08779 0.08287 -0.0976 0.1138 1.0000
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