EPPLER 403 AIRFOIL (e403-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 403 AIRFOIL (e403-il) Reynolds number: 1,000,000 Max Cl/Cd: 138.59 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e403-il-1000000.txt Download as CSV file: xf-e403-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 403 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4758 0.04494 0.04206 -0.1495 0.9741 0.0134
-12.000 -0.4668 0.04206 0.03911 -0.1524 0.9733 0.0136
-11.750 -0.4749 0.03910 0.03599 -0.1527 0.9690 0.0136
-11.500 -0.4623 0.03780 0.03470 -0.1535 0.9664 0.0139
-11.250 -0.4565 0.03559 0.03238 -0.1549 0.9636 0.0142
-11.000 -0.4875 0.02661 0.02233 -0.1530 0.9581 0.0101
-10.750 -0.4846 0.02546 0.02106 -0.1505 0.9535 0.0100
-10.500 -0.4734 0.02443 0.01992 -0.1494 0.9503 0.0100
-10.250 -0.4582 0.02325 0.01861 -0.1488 0.9480 0.0099
-10.000 -0.4391 0.02202 0.01727 -0.1486 0.9463 0.0099
-9.750 -0.4185 0.02087 0.01601 -0.1481 0.9445 0.0099
-9.500 -0.3962 0.01952 0.01459 -0.1473 0.9434 0.0101
-9.250 -0.3821 0.01865 0.01367 -0.1453 0.9409 0.0102
-9.000 -0.3685 0.01801 0.01297 -0.1436 0.9380 0.0102
-8.750 -0.3545 0.01721 0.01213 -0.1420 0.9355 0.0103
-8.500 -0.3399 0.01642 0.01131 -0.1407 0.9331 0.0105
-8.250 -0.3220 0.01570 0.01054 -0.1403 0.9310 0.0107
-8.000 -0.3104 0.01518 0.01000 -0.1386 0.9280 0.0110
-7.750 -0.2957 0.01459 0.00936 -0.1374 0.9248 0.0111
-7.500 -0.2759 0.01402 0.00876 -0.1370 0.9224 0.0115
-7.250 -0.2529 0.01350 0.00820 -0.1371 0.9207 0.0119
-7.000 -0.2281 0.01297 0.00762 -0.1375 0.9192 0.0122
-6.750 -0.2015 0.01250 0.00711 -0.1381 0.9179 0.0126
-6.500 -0.1743 0.01212 0.00668 -0.1388 0.9164 0.0128
-6.250 -0.1518 0.01173 0.00625 -0.1385 0.9145 0.0132
-6.000 -0.1292 0.01131 0.00579 -0.1382 0.9122 0.0138
-5.750 -0.1037 0.01098 0.00545 -0.1383 0.9101 0.0151
-5.500 -0.0764 0.01071 0.00515 -0.1387 0.9084 0.0163
-5.250 -0.0476 0.01039 0.00480 -0.1394 0.9070 0.0191
-5.000 -0.0180 0.00974 0.00437 -0.1408 0.9056 0.0630
-4.750 0.0136 0.00867 0.00381 -0.1432 0.9044 0.1967
-4.500 0.0485 0.00730 0.00318 -0.1467 0.9034 0.3982
-4.250 0.0816 0.00685 0.00301 -0.1486 0.9024 0.4913
-4.000 0.1122 0.00680 0.00302 -0.1494 0.9010 0.5201
-3.750 0.1396 0.00679 0.00302 -0.1495 0.8992 0.5380
-3.500 0.1675 0.00679 0.00304 -0.1497 0.8970 0.5533
-3.250 0.1965 0.00680 0.00305 -0.1500 0.8949 0.5664
-3.000 0.2269 0.00682 0.00302 -0.1506 0.8929 0.5761
-2.750 0.2579 0.00675 0.00297 -0.1513 0.8910 0.5826
-2.500 0.2901 0.00671 0.00288 -0.1522 0.8890 0.5881
-2.250 0.3222 0.00668 0.00280 -0.1532 0.8865 0.5922
-2.000 0.3481 0.00661 0.00276 -0.1529 0.8828 0.5955
-1.750 0.3771 0.00654 0.00269 -0.1532 0.8793 0.5981
-1.500 0.4079 0.00646 0.00259 -0.1538 0.8764 0.6007
-1.250 0.4391 0.00640 0.00249 -0.1546 0.8739 0.6032
-1.000 0.4693 0.00639 0.00245 -0.1552 0.8713 0.6055
-0.750 0.4962 0.00635 0.00243 -0.1551 0.8678 0.6077
-0.500 0.5249 0.00629 0.00239 -0.1554 0.8643 0.6100
-0.250 0.5548 0.00624 0.00234 -0.1559 0.8612 0.6121
0.000 0.5858 0.00619 0.00229 -0.1566 0.8581 0.6142
0.250 0.6122 0.00618 0.00230 -0.1564 0.8533 0.6165
0.500 0.6403 0.00614 0.00225 -0.1565 0.8480 0.6188
0.750 0.6710 0.00610 0.00218 -0.1572 0.8433 0.6208
1.000 0.6966 0.00608 0.00220 -0.1568 0.8367 0.6227
1.250 0.7252 0.00603 0.00216 -0.1570 0.8307 0.6250
1.500 0.7519 0.00603 0.00218 -0.1568 0.8232 0.6271
1.750 0.7801 0.00603 0.00217 -0.1569 0.8149 0.6291
2.000 0.8061 0.00604 0.00220 -0.1566 0.8037 0.6311
2.250 0.8321 0.00609 0.00222 -0.1562 0.7893 0.6333
2.500 0.8565 0.00618 0.00224 -0.1555 0.7685 0.6354
2.750 0.8785 0.00634 0.00230 -0.1543 0.7411 0.6372
3.000 0.8972 0.00656 0.00239 -0.1524 0.7056 0.6393
3.250 0.9110 0.00692 0.00257 -0.1495 0.6626 0.6413
3.500 0.9228 0.00733 0.00281 -0.1462 0.6202 0.6433
3.750 0.9322 0.00773 0.00304 -0.1425 0.5784 0.6454
4.000 0.9421 0.00819 0.00331 -0.1389 0.5358 0.6476
4.250 0.9521 0.00876 0.00365 -0.1355 0.4854 0.6496
4.500 0.9641 0.00937 0.00401 -0.1326 0.4340 0.6515
4.750 0.9785 0.00995 0.00436 -0.1302 0.3864 0.6530
5.000 0.9953 0.01044 0.00468 -0.1284 0.3454 0.6554
5.250 1.0143 0.01086 0.00498 -0.1269 0.3152 0.6575
5.500 1.0323 0.01135 0.00533 -0.1253 0.2811 0.6596
5.750 1.0501 0.01188 0.00570 -0.1237 0.2454 0.6617
6.000 1.0679 0.01242 0.00609 -0.1222 0.2116 0.6637
6.250 1.0864 0.01295 0.00647 -0.1208 0.1827 0.6657
6.500 1.1043 0.01354 0.00691 -0.1193 0.1516 0.6676
6.750 1.1205 0.01423 0.00740 -0.1175 0.1169 0.6694
7.000 1.1378 0.01485 0.00789 -0.1160 0.0903 0.6719
7.250 1.1541 0.01556 0.00846 -0.1143 0.0625 0.6740
7.500 1.1681 0.01647 0.00917 -0.1123 0.0324 0.6760
7.750 1.1829 0.01733 0.00991 -0.1104 0.0157 0.6781
8.000 1.2019 0.01787 0.01047 -0.1091 0.0134 0.6803
8.250 1.2211 0.01840 0.01103 -0.1079 0.0124 0.6823
8.500 1.2393 0.01901 0.01168 -0.1065 0.0114 0.6840
8.750 1.2560 0.01973 0.01247 -0.1049 0.0107 0.6865
9.000 1.2743 0.02029 0.01311 -0.1037 0.0105 0.6889
9.250 1.2922 0.02090 0.01378 -0.1023 0.0101 0.6913
9.500 1.3093 0.02157 0.01450 -0.1010 0.0097 0.6936
9.750 1.3255 0.02230 0.01528 -0.0995 0.0094 0.6959
10.000 1.3407 0.02311 0.01615 -0.0978 0.0091 0.6980
10.250 1.3552 0.02398 0.01707 -0.0962 0.0088 0.7000
10.500 1.3673 0.02501 0.01819 -0.0942 0.0085 0.7026
10.750 1.3773 0.02622 0.01951 -0.0920 0.0083 0.7051
11.000 1.3825 0.02779 0.02119 -0.0893 0.0081 0.7075
11.250 1.3891 0.02932 0.02282 -0.0869 0.0080 0.7100
11.500 1.4003 0.03046 0.02404 -0.0852 0.0079 0.7125
11.750 1.4110 0.03169 0.02534 -0.0834 0.0079 0.7146
12.000 1.4210 0.03298 0.02673 -0.0817 0.0078 0.7173
12.250 1.4298 0.03441 0.02826 -0.0799 0.0077 0.7199
12.500 1.4376 0.03594 0.02989 -0.0781 0.0076 0.7226
12.750 1.4446 0.03758 0.03163 -0.0764 0.0075 0.7254
13.000 1.4509 0.03935 0.03350 -0.0747 0.0074 0.7282
13.250 1.4566 0.04122 0.03546 -0.0730 0.0073 0.7309
13.500 1.4613 0.04324 0.03759 -0.0715 0.0072 0.7339
13.750 1.4653 0.04540 0.03987 -0.0701 0.0071 0.7368
14.000 1.4690 0.04766 0.04224 -0.0688 0.0070 0.7399
14.250 1.4717 0.05010 0.04479 -0.0676 0.0069 0.7429
14.500 1.4741 0.05263 0.04743 -0.0666 0.0068 0.7459
14.750 1.4761 0.05529 0.05021 -0.0658 0.0067 0.7494
15.000 1.4772 0.05816 0.05319 -0.0652 0.0066 0.7530
15.250 1.4774 0.06122 0.05636 -0.0648 0.0065 0.7569
15.500 1.4764 0.06456 0.05981 -0.0646 0.0064 0.7605
15.750 1.4742 0.06819 0.06356 -0.0647 0.0063 0.7643
16.000 1.4705 0.07216 0.06766 -0.0650 0.0062 0.7683
16.250 1.4655 0.07647 0.07210 -0.0656 0.0062 0.7724
16.500 1.4597 0.08107 0.07683 -0.0665 0.0061 0.7763
16.750 1.4523 0.08605 0.08196 -0.0678 0.0061 0.7805
17.000 1.4433 0.09145 0.08752 -0.0694 0.0060 0.7849
17.250 1.4331 0.09720 0.09341 -0.0714 0.0060 0.7893
17.500 1.4234 0.10307 0.09945 -0.0738 0.0060 0.7941
17.750 1.4126 0.10932 0.10587 -0.0766 0.0059 0.7996
18.000 1.4005 0.11591 0.11263 -0.0798 0.0059 0.8052
18.250 1.3885 0.12271 0.11960 -0.0835 0.0059 0.8116
18.500 1.3751 0.12995 0.12702 -0.0877 0.0059 0.8189
18.750 1.3632 0.13713 0.13437 -0.0921 0.0059 0.8276
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