EPPLER 542 AIRFOIL (e542-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 542 AIRFOIL (e542-il) Reynolds number: 200,000 Max Cl/Cd: 54.92 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e542-il-200000-n5.txt Download as CSV file: xf-e542-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 542 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4517 0.10385 0.10020 -0.0547 1.0000 0.0094
-12.750 -0.4766 0.09063 0.08699 -0.0608 1.0000 0.0094
-12.500 -0.4835 0.08489 0.08127 -0.0645 1.0000 0.0091
-12.250 -0.5037 0.07731 0.07361 -0.0689 1.0000 0.0089
-12.000 -0.5296 0.07073 0.06693 -0.0715 1.0000 0.0087
-11.750 -0.5566 0.06526 0.06134 -0.0719 1.0000 0.0084
-11.500 -0.5813 0.06086 0.05679 -0.0709 1.0000 0.0086
-11.250 -0.6080 0.05676 0.05251 -0.0684 1.0000 0.0087
-11.000 -0.6354 0.05293 0.04851 -0.0647 1.0000 0.0081
-10.750 -0.6465 0.04972 0.04508 -0.0631 0.9961 0.0085
-10.500 -0.6514 0.04562 0.04065 -0.0625 0.9784 0.0084
-10.250 -0.6567 0.04099 0.03540 -0.0613 0.9602 0.0092
-10.000 -0.6441 0.03761 0.03159 -0.0618 0.9483 0.0092
-9.750 -0.6244 0.03428 0.02765 -0.0627 0.9382 0.0094
-9.500 -0.5955 0.03150 0.02454 -0.0646 0.9293 0.0096
-9.250 -0.5624 0.02946 0.02224 -0.0668 0.9201 0.0097
-9.000 -0.5246 0.02753 0.02005 -0.0694 0.9118 0.0099
-8.750 -0.4887 0.02602 0.01834 -0.0716 0.9017 0.0102
-8.500 -0.4520 0.02465 0.01680 -0.0738 0.8916 0.0107
-8.250 -0.4191 0.02349 0.01548 -0.0753 0.8801 0.0110
-8.000 -0.3911 0.02251 0.01432 -0.0758 0.8680 0.0117
-7.750 -0.3674 0.02164 0.01335 -0.0758 0.8563 0.0122
-7.500 -0.3460 0.02092 0.01254 -0.0753 0.8453 0.0129
-7.250 -0.3273 0.02027 0.01180 -0.0742 0.8343 0.0141
-7.000 -0.3085 0.01967 0.01107 -0.0731 0.8245 0.0151
-6.750 -0.2901 0.01917 0.01048 -0.0718 0.8146 0.0180
-6.500 -0.2727 0.01865 0.00992 -0.0704 0.8056 0.0218
-6.250 -0.2562 0.01809 0.00932 -0.0688 0.7971 0.0274
-6.000 -0.2407 0.01753 0.00879 -0.0671 0.7893 0.0391
-5.750 -0.2272 0.01692 0.00830 -0.0650 0.7816 0.0642
-5.500 -0.2151 0.01631 0.00786 -0.0627 0.7745 0.1034
-5.250 -0.2076 0.01559 0.00740 -0.0598 0.7668 0.1628
-5.000 -0.2061 0.01476 0.00688 -0.0557 0.7601 0.2407
-4.750 -0.2170 0.01393 0.00646 -0.0493 0.7523 0.3294
-4.500 -0.1649 0.01567 0.00990 -0.0494 0.7484 0.6597
-4.250 -0.1654 0.01548 0.00962 -0.0445 0.7426 0.6902
-4.000 -0.1740 0.01495 0.00901 -0.0385 0.7356 0.7125
-3.750 -0.1668 0.01487 0.00878 -0.0349 0.7301 0.7305
-3.500 -0.1460 0.01543 0.00922 -0.0330 0.7249 0.7454
-3.250 -0.0954 0.01720 0.01089 -0.0351 0.7200 0.7562
-3.000 -0.0450 0.01860 0.01216 -0.0375 0.7159 0.7657
-2.750 -0.0416 0.01834 0.01178 -0.0335 0.7116 0.7766
-2.500 -0.0117 0.01841 0.01177 -0.0338 0.7065 0.7778
-2.250 0.0175 0.01843 0.01170 -0.0341 0.7017 0.7791
-2.000 0.0457 0.01842 0.01158 -0.0343 0.6976 0.7807
-1.750 0.0715 0.01838 0.01144 -0.0341 0.6936 0.7827
-1.250 0.0940 0.01775 0.01069 -0.0292 0.6845 0.7931
-1.000 0.1218 0.01771 0.01056 -0.0293 0.6808 0.7940
-0.750 0.1483 0.01768 0.01048 -0.0293 0.6768 0.7951
-0.500 0.1735 0.01765 0.01042 -0.0290 0.6725 0.7965
-0.250 0.1978 0.01757 0.01030 -0.0286 0.6686 0.7980
0.000 0.2220 0.01749 0.01015 -0.0282 0.6650 0.7998
0.250 0.2439 0.01736 0.00999 -0.0275 0.6614 0.8020
0.500 0.2611 0.01715 0.00976 -0.0261 0.6571 0.8050
0.750 0.2765 0.01682 0.00939 -0.0247 0.6530 0.8087
1.000 0.3023 0.01675 0.00929 -0.0246 0.6495 0.8095
1.250 0.3290 0.01672 0.00922 -0.0246 0.6463 0.8103
1.500 0.3524 0.01671 0.00924 -0.0240 0.6419 0.8114
1.750 0.3766 0.01666 0.00921 -0.0237 0.6376 0.8125
2.000 0.4016 0.01660 0.00913 -0.0235 0.6339 0.8134
2.250 0.4280 0.01655 0.00904 -0.0236 0.6306 0.8144
2.500 0.4497 0.01650 0.00905 -0.0228 0.6257 0.8158
2.750 0.4730 0.01645 0.00903 -0.0223 0.6209 0.8174
3.000 0.4979 0.01637 0.00893 -0.0222 0.6166 0.8188
3.250 0.5217 0.01630 0.00887 -0.0219 0.6117 0.8201
3.500 0.5443 0.01621 0.00883 -0.0215 0.6060 0.8216
3.750 0.5694 0.01612 0.00874 -0.0215 0.6011 0.8229
4.000 0.5945 0.01605 0.00868 -0.0215 0.5960 0.8244
4.500 0.6421 0.01603 0.00876 -0.0205 0.5841 0.8260
4.750 0.6651 0.01603 0.00883 -0.0199 0.5777 0.8268
5.000 0.6880 0.01602 0.00888 -0.0193 0.5707 0.8276
5.250 0.7124 0.01601 0.00890 -0.0189 0.5642 0.8284
5.500 0.7338 0.01601 0.00899 -0.0181 0.5560 0.8294
5.750 0.7573 0.01600 0.00902 -0.0176 0.5483 0.8303
6.000 0.7783 0.01601 0.00911 -0.0166 0.5388 0.8314
6.250 0.7999 0.01602 0.00919 -0.0158 0.5293 0.8324
6.500 0.8213 0.01603 0.00923 -0.0149 0.5189 0.8337
6.750 0.8403 0.01608 0.00936 -0.0136 0.5066 0.8352
7.000 0.8591 0.01613 0.00947 -0.0124 0.4929 0.8367
7.250 0.8768 0.01620 0.00956 -0.0109 0.4766 0.8379
7.500 0.8921 0.01631 0.00966 -0.0090 0.4572 0.8391
7.750 0.9035 0.01645 0.00980 -0.0063 0.4355 0.8403
8.000 0.9104 0.01671 0.00999 -0.0028 0.4113 0.8414
8.250 0.9166 0.01712 0.01035 0.0006 0.3855 0.8426
8.500 0.9209 0.01770 0.01084 0.0041 0.3590 0.8439
8.750 0.9244 0.01839 0.01145 0.0075 0.3333 0.8454
9.000 0.9281 0.01915 0.01214 0.0106 0.3088 0.8469
9.250 0.9310 0.02002 0.01294 0.0136 0.2858 0.8488
9.500 0.9346 0.02096 0.01383 0.0163 0.2629 0.8507
9.750 0.9386 0.02198 0.01480 0.0186 0.2419 0.8522
10.000 0.9417 0.02314 0.01589 0.0208 0.2209 0.8537
10.250 0.9460 0.02432 0.01703 0.0227 0.2006 0.8551
10.500 0.9485 0.02561 0.01826 0.0248 0.1809 0.8564
10.750 0.9515 0.02693 0.01955 0.0267 0.1638 0.8576
11.000 0.9550 0.02830 0.02089 0.0283 0.1469 0.8589
11.250 0.9594 0.02968 0.02227 0.0298 0.1316 0.8603
11.500 0.9639 0.03113 0.02370 0.0311 0.1177 0.8617
11.750 0.9688 0.03261 0.02518 0.0322 0.1054 0.8632
12.000 0.9732 0.03417 0.02674 0.0333 0.0941 0.8647
12.250 0.9788 0.03572 0.02830 0.0342 0.0838 0.8664
12.500 0.9844 0.03732 0.02994 0.0350 0.0749 0.8682
12.750 0.9896 0.03902 0.03167 0.0356 0.0672 0.8698
13.000 0.9936 0.04086 0.03353 0.0363 0.0599 0.8713
13.250 0.9979 0.04265 0.03538 0.0369 0.0535 0.8726
13.500 1.0022 0.04452 0.03732 0.0375 0.0481 0.8740
13.750 1.0049 0.04662 0.03945 0.0379 0.0435 0.8755
14.000 1.0095 0.04863 0.04156 0.0382 0.0392 0.8770
14.250 1.0118 0.05093 0.04392 0.0383 0.0359 0.8787
14.500 1.0156 0.05316 0.04623 0.0383 0.0324 0.8803
14.750 1.0184 0.05558 0.04872 0.0382 0.0297 0.8820
15.000 1.0215 0.05807 0.05129 0.0379 0.0271 0.8837
15.250 1.0229 0.06081 0.05412 0.0374 0.0250 0.8854
15.500 1.0255 0.06345 0.05687 0.0370 0.0228 0.8870
15.750 1.0247 0.06653 0.06003 0.0364 0.0215 0.8886
16.000 1.0265 0.06939 0.06305 0.0358 0.0197 0.8905
16.250 1.0258 0.07265 0.06641 0.0349 0.0185 0.8923
16.500 1.0240 0.07613 0.07001 0.0339 0.0173 0.8944
16.750 1.0237 0.07953 0.07354 0.0328 0.0160 0.8967
17.000 1.0204 0.08345 0.07757 0.0314 0.0149 0.8989
17.500 1.0138 0.09152 0.08594 0.0283 0.0132 0.9035
17.750 1.0096 0.09584 0.09038 0.0265 0.0123 0.9062
18.000 1.0031 0.10061 0.09526 0.0244 0.0118 0.9090
18.250 0.9982 0.10523 0.10005 0.0223 0.0114 0.9119
18.500 0.9932 0.11001 0.10499 0.0199 0.0105 0.9150
18.750 0.9869 0.11507 0.11019 0.0173 0.0099 0.9184
19.000 0.9789 0.12052 0.11575 0.0144 0.0094 0.9225
19.250 0.9726 0.12573 0.12114 0.0116 0.0092 0.9275
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