EPPLER EA 6(-1)-009 AIRFOIL (ea61009-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER EA 6(-1)-009 AIRFOIL (ea61009-il) Reynolds number: 500,000 Max Cl/Cd: 58.37 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ea61009-il-500000-n5.txt Download as CSV file: xf-ea61009-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER EA 6(-1)-009 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
------ -------- --------- --------- -------- -------- --------
-15.500 -0.8575 0.14930 0.14695 0.0412 1.0000 0.0092
-15.250 -1.1701 0.06964 0.06673 -0.0067 1.0000 0.0072
-15.000 -1.2087 0.05791 0.05471 -0.0154 1.0000 0.0071
-14.750 -1.2295 0.05120 0.04782 -0.0196 1.0000 0.0071
-14.500 -1.2463 0.04604 0.04246 -0.0220 1.0000 0.0072
-14.250 -1.2581 0.04211 0.03836 -0.0229 1.0000 0.0072
-14.000 -1.2658 0.03902 0.03513 -0.0229 1.0000 0.0074
-13.750 -1.2708 0.03649 0.03246 -0.0221 1.0000 0.0075
-13.500 -1.2738 0.03438 0.03020 -0.0208 1.0000 0.0076
-13.250 -1.2749 0.03262 0.02830 -0.0188 1.0000 0.0078
-13.000 -1.2725 0.03111 0.02666 -0.0166 1.0000 0.0080
-12.750 -1.2641 0.02963 0.02502 -0.0152 1.0000 0.0082
-12.500 -1.2526 0.02824 0.02348 -0.0139 1.0000 0.0085
-12.250 -1.2390 0.02693 0.02201 -0.0128 1.0000 0.0088
-12.000 -1.2234 0.02571 0.02064 -0.0119 1.0000 0.0091
-11.750 -1.2061 0.02461 0.01938 -0.0110 1.0000 0.0093
-11.500 -1.1885 0.02347 0.01808 -0.0102 1.0000 0.0098
-11.250 -1.1700 0.02235 0.01684 -0.0094 1.0000 0.0105
-11.000 -1.1500 0.02137 0.01578 -0.0087 1.0000 0.0115
-10.750 -1.1290 0.02049 0.01483 -0.0082 1.0000 0.0125
-10.500 -1.1071 0.01969 0.01394 -0.0076 1.0000 0.0135
-10.250 -1.0847 0.01894 0.01305 -0.0071 1.0000 0.0145
-10.000 -1.0615 0.01829 0.01237 -0.0067 1.0000 0.0176
-9.750 -1.0371 0.01784 0.01192 -0.0064 1.0000 0.0206
-9.500 -1.0127 0.01735 0.01136 -0.0061 1.0000 0.0230
-9.250 -0.9874 0.01701 0.01099 -0.0059 1.0000 0.0250
-9.000 -0.9605 0.01698 0.01097 -0.0058 1.0000 0.0273
-8.750 -0.9345 0.01674 0.01067 -0.0057 1.0000 0.0293
-8.500 -0.9087 0.01643 0.01027 -0.0054 1.0000 0.0308
-8.250 -0.8831 0.01606 0.00985 -0.0052 1.0000 0.0318
-8.000 -0.8564 0.01593 0.00973 -0.0052 1.0000 0.0331
-7.750 -0.8295 0.01585 0.00959 -0.0051 1.0000 0.0343
-7.500 -0.8028 0.01567 0.00937 -0.0051 1.0000 0.0356
-7.250 -0.7761 0.01549 0.00915 -0.0050 1.0000 0.0370
-7.000 -0.7492 0.01532 0.00892 -0.0049 1.0000 0.0382
-6.750 -0.7219 0.01525 0.00880 -0.0049 1.0000 0.0391
-6.500 -0.6929 0.01449 0.00799 -0.0055 0.9694 0.0402
-6.250 -0.6603 0.01382 0.00725 -0.0068 0.9436 0.0412
-6.000 -0.6329 0.01340 0.00678 -0.0069 0.9259 0.0420
-5.750 -0.6075 0.01306 0.00637 -0.0064 0.9127 0.0427
-5.500 -0.5821 0.01274 0.00599 -0.0059 0.9023 0.0434
-5.250 -0.5564 0.01242 0.00562 -0.0055 0.8940 0.0441
-5.000 -0.5307 0.01212 0.00526 -0.0052 0.8863 0.0449
-4.750 -0.5045 0.01182 0.00492 -0.0048 0.8794 0.0457
-4.500 -0.4783 0.01154 0.00460 -0.0045 0.8727 0.0466
-4.250 -0.4517 0.01131 0.00433 -0.0043 0.8668 0.0478
-4.000 -0.4248 0.01110 0.00407 -0.0041 0.8601 0.0489
-3.750 -0.3982 0.01089 0.00382 -0.0037 0.8534 0.0497
-3.500 -0.3712 0.01067 0.00358 -0.0035 0.8459 0.0503
-3.250 -0.3444 0.01049 0.00336 -0.0033 0.8397 0.0507
-3.000 -0.3172 0.01024 0.00309 -0.0032 0.8334 0.0516
-2.750 -0.2907 0.00999 0.00281 -0.0028 0.8236 0.0529
-2.500 -0.2641 0.00980 0.00258 -0.0024 0.8095 0.0542
-2.250 -0.2370 0.00963 0.00239 -0.0022 0.7961 0.0557
-2.000 -0.2096 0.00948 0.00222 -0.0020 0.7854 0.0572
-1.750 -0.1822 0.00936 0.00207 -0.0018 0.7732 0.0588
-1.500 -0.1547 0.00926 0.00193 -0.0016 0.7605 0.0604
-1.250 -0.1273 0.00913 0.00178 -0.0014 0.7430 0.0638
-1.000 -0.1005 0.00905 0.00163 -0.0011 0.7121 0.0692
-0.750 -0.0750 0.00862 0.00142 -0.0007 0.6733 0.1647
-0.250 -0.0242 0.00797 0.00116 -0.0003 0.5788 0.3645
0.000 0.0000 0.00814 0.00111 0.0000 0.4421 0.4423
0.250 0.0241 0.00797 0.00116 0.0003 0.3646 0.5791
0.500 0.0487 0.00847 0.00130 0.0005 0.2147 0.6331
0.750 0.0750 0.00862 0.00142 0.0007 0.1640 0.6730
1.000 0.1004 0.00905 0.00163 0.0011 0.0692 0.7121
1.250 0.1273 0.00913 0.00178 0.0014 0.0638 0.7429
1.500 0.1547 0.00926 0.00193 0.0016 0.0604 0.7605
1.750 0.1822 0.00936 0.00207 0.0018 0.0588 0.7731
2.000 0.2096 0.00948 0.00222 0.0020 0.0572 0.7853
2.250 0.2370 0.00963 0.00239 0.0022 0.0557 0.7963
2.500 0.2641 0.00980 0.00258 0.0025 0.0542 0.8096
2.750 0.2907 0.00999 0.00281 0.0028 0.0529 0.8237
3.000 0.3171 0.01024 0.00309 0.0032 0.0516 0.8334
3.250 0.3443 0.01050 0.00336 0.0033 0.0507 0.8397
3.500 0.3711 0.01067 0.00358 0.0036 0.0503 0.8460
3.750 0.3982 0.01089 0.00382 0.0038 0.0497 0.8535
4.000 0.4247 0.01110 0.00407 0.0041 0.0489 0.8601
4.250 0.4516 0.01131 0.00433 0.0043 0.0478 0.8668
4.500 0.4782 0.01154 0.00459 0.0045 0.0465 0.8726
4.750 0.5044 0.01182 0.00491 0.0049 0.0457 0.8793
5.000 0.5305 0.01212 0.00526 0.0052 0.0448 0.8863
5.250 0.5563 0.01242 0.00562 0.0056 0.0441 0.8940
5.500 0.5819 0.01274 0.00599 0.0060 0.0434 0.9023
5.750 0.6073 0.01306 0.00637 0.0064 0.0427 0.9128
6.000 0.6327 0.01340 0.00678 0.0069 0.0420 0.9259
6.250 0.6601 0.01381 0.00725 0.0069 0.0412 0.9438
6.500 0.6927 0.01448 0.00798 0.0056 0.0402 0.9696
6.750 0.7217 0.01526 0.00881 0.0049 0.0391 1.0000
7.000 0.7489 0.01533 0.00893 0.0050 0.0383 1.0000
7.250 0.7758 0.01548 0.00913 0.0050 0.0370 1.0000
7.500 0.8026 0.01565 0.00935 0.0051 0.0356 1.0000
7.750 0.8291 0.01585 0.00959 0.0052 0.0343 1.0000
8.000 0.8561 0.01593 0.00972 0.0053 0.0331 1.0000
8.250 0.8826 0.01607 0.00986 0.0053 0.0319 1.0000
8.500 0.9083 0.01642 0.01026 0.0055 0.0308 1.0000
8.750 0.9340 0.01674 0.01067 0.0057 0.0293 1.0000
9.000 0.9600 0.01697 0.01096 0.0059 0.0273 1.0000
9.250 0.9869 0.01701 0.01099 0.0060 0.0250 1.0000
9.500 1.0122 0.01734 0.01135 0.0062 0.0231 1.0000
9.750 1.0365 0.01784 0.01191 0.0065 0.0206 1.0000
10.000 1.0610 0.01828 0.01236 0.0068 0.0175 1.0000
10.250 1.0842 0.01894 0.01304 0.0072 0.0145 1.0000
10.500 1.1066 0.01968 0.01393 0.0078 0.0136 1.0000
10.750 1.1283 0.02048 0.01482 0.0083 0.0125 1.0000
11.000 1.1493 0.02135 0.01577 0.0089 0.0115 1.0000
11.250 1.1691 0.02235 0.01684 0.0095 0.0105 1.0000
11.500 1.1877 0.02344 0.01805 0.0103 0.0098 1.0000
11.750 1.2052 0.02459 0.01936 0.0112 0.0093 1.0000
12.000 1.2224 0.02570 0.02063 0.0120 0.0091 1.0000
12.250 1.2380 0.02690 0.02199 0.0130 0.0088 1.0000
12.500 1.2517 0.02821 0.02345 0.0141 0.0085 1.0000
12.750 1.2630 0.02961 0.02500 0.0154 0.0082 1.0000
13.000 1.2713 0.03110 0.02665 0.0169 0.0080 1.0000
13.250 1.2736 0.03261 0.02829 0.0191 0.0078 1.0000
13.500 1.2723 0.03439 0.03023 0.0210 0.0077 1.0000
13.750 1.2693 0.03652 0.03249 0.0223 0.0075 1.0000
14.000 1.2656 0.03894 0.03505 0.0230 0.0074 1.0000
14.250 1.2579 0.04204 0.03829 0.0230 0.0072 1.0000
14.500 1.2461 0.04596 0.04239 0.0221 0.0072 1.0000
14.750 1.2286 0.05124 0.04786 0.0197 0.0072 1.0000
15.000 1.2078 0.05795 0.05476 0.0154 0.0071 1.0000
15.250 1.1701 0.06956 0.06664 0.0068 0.0072 1.0000
15.500 0.8574 0.14938 0.14703 -0.0412 0.0093 1.0000
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Polar data table (+)
Polar graphs
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