EPPLER 520 AIRFOIL (e520-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 520 AIRFOIL (e520-il) Reynolds number: 200,000 Max Cl/Cd: 45.16 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e520-il-200000-n5.txt Download as CSV file: xf-e520-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 520 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
------ -------- --------- --------- -------- -------- --------
-18.500 -0.8741 0.15125 0.14736 0.0200 1.0000 0.0103
-18.250 -0.8893 0.14262 0.13860 0.0150 1.0000 0.0103
-18.000 -0.9048 0.13418 0.13003 0.0100 1.0000 0.0104
-17.750 -0.9172 0.12674 0.12246 0.0057 1.0000 0.0104
-17.500 -0.9289 0.11974 0.11534 0.0017 1.0000 0.0104
-17.250 -0.9410 0.11281 0.10830 -0.0023 1.0000 0.0106
-17.000 -0.9520 0.10626 0.10162 -0.0060 1.0000 0.0107
-16.750 -0.9631 0.09984 0.09508 -0.0096 1.0000 0.0109
-16.500 -0.9733 0.09378 0.08889 -0.0129 1.0000 0.0110
-16.250 -0.9825 0.08801 0.08300 -0.0160 1.0000 0.0112
-16.000 -0.9903 0.08270 0.07755 -0.0188 1.0000 0.0114
-15.750 -0.9981 0.07758 0.07230 -0.0213 1.0000 0.0116
-15.500 -1.0039 0.07295 0.06754 -0.0235 1.0000 0.0118
-15.250 -1.0084 0.06865 0.06311 -0.0254 1.0000 0.0122
-15.000 -1.0128 0.06458 0.05889 -0.0270 1.0000 0.0126
-14.750 -1.0141 0.06103 0.05520 -0.0283 1.0000 0.0132
-14.500 -1.0157 0.05763 0.05163 -0.0292 1.0000 0.0138
-14.250 -1.0191 0.05418 0.04807 -0.0301 1.0000 0.0143
-14.000 -1.0221 0.05097 0.04478 -0.0307 1.0000 0.0149
-13.750 -1.0214 0.04829 0.04202 -0.0311 1.0000 0.0157
-13.500 -1.0197 0.04581 0.03943 -0.0312 1.0000 0.0163
-13.250 -1.0167 0.04353 0.03704 -0.0312 1.0000 0.0174
-13.000 -1.0131 0.04138 0.03474 -0.0309 1.0000 0.0181
-12.750 -1.0102 0.03921 0.03246 -0.0305 1.0000 0.0191
-12.500 -1.0076 0.03711 0.03033 -0.0301 1.0000 0.0203
-12.250 -1.0000 0.03550 0.02865 -0.0297 1.0000 0.0220
-12.000 -0.9921 0.03393 0.02698 -0.0291 1.0000 0.0237
-11.750 -0.9840 0.03241 0.02537 -0.0284 1.0000 0.0253
-11.500 -0.9787 0.03071 0.02365 -0.0275 1.0000 0.0272
-11.250 -0.9688 0.02938 0.02227 -0.0268 1.0000 0.0296
-11.000 -0.9571 0.02821 0.02101 -0.0261 1.0000 0.0322
-10.750 -0.9486 0.02683 0.01963 -0.0252 1.0000 0.0349
-10.500 -0.9371 0.02568 0.01844 -0.0244 1.0000 0.0387
-10.000 -0.9011 0.02357 0.01611 -0.0250 0.8962 0.0486
-9.500 -0.8772 0.02191 0.01430 -0.0220 0.8683 0.0608
-9.250 -0.8651 0.02117 0.01349 -0.0204 0.8588 0.0679
-9.000 -0.8531 0.02053 0.01279 -0.0184 0.8510 0.0765
-8.750 -0.8415 0.01990 0.01214 -0.0165 0.8441 0.0864
-8.500 -0.8272 0.01930 0.01152 -0.0148 0.8384 0.0976
-8.250 -0.8114 0.01871 0.01093 -0.0134 0.8334 0.1112
-8.000 -0.7941 0.01813 0.01037 -0.0123 0.8280 0.1268
-7.750 -0.7765 0.01759 0.00984 -0.0111 0.8235 0.1448
-7.500 -0.7586 0.01704 0.00933 -0.0099 0.8196 0.1639
-7.250 -0.7393 0.01651 0.00884 -0.0090 0.8154 0.1855
-7.000 -0.7199 0.01599 0.00838 -0.0081 0.8112 0.2082
-6.750 -0.7001 0.01551 0.00795 -0.0071 0.8077 0.2337
-6.500 -0.6793 0.01504 0.00755 -0.0063 0.8043 0.2602
-6.250 -0.6581 0.01458 0.00717 -0.0056 0.8006 0.2883
-6.000 -0.6366 0.01414 0.00680 -0.0049 0.7970 0.3188
-5.750 -0.6148 0.01373 0.00647 -0.0042 0.7938 0.3501
-5.500 -0.5926 0.01335 0.00618 -0.0035 0.7910 0.3821
-5.250 -0.5692 0.01299 0.00594 -0.0030 0.7875 0.4146
-5.000 -0.5454 0.01269 0.00572 -0.0025 0.7840 0.4473
-4.750 -0.5211 0.01244 0.00556 -0.0019 0.7809 0.4782
-4.500 -0.4963 0.01226 0.00545 -0.0014 0.7782 0.5077
-4.250 -0.4705 0.01214 0.00541 -0.0011 0.7754 0.5353
-4.000 -0.4439 0.01208 0.00539 -0.0008 0.7718 0.5592
-3.750 -0.4170 0.01207 0.00540 -0.0006 0.7685 0.5795
-3.500 -0.3899 0.01208 0.00539 -0.0004 0.7656 0.5968
-3.250 -0.3626 0.01212 0.00538 -0.0002 0.7629 0.6115
-3.000 -0.3349 0.01217 0.00542 -0.0002 0.7595 0.6241
-2.750 -0.3071 0.01221 0.00545 -0.0002 0.7557 0.6352
-2.500 -0.2793 0.01225 0.00543 -0.0001 0.7521 0.6459
-2.250 -0.2516 0.01231 0.00543 0.0000 0.7490 0.6552
-2.000 -0.2237 0.01237 0.00547 0.0000 0.7457 0.6631
-1.750 -0.1958 0.01240 0.00547 -0.0001 0.7413 0.6717
-1.500 -0.1678 0.01246 0.00551 0.0000 0.7375 0.6778
-1.250 -0.1399 0.01249 0.00549 0.0000 0.7341 0.6850
-1.000 -0.1119 0.01253 0.00551 0.0000 0.7303 0.6909
-0.750 -0.0839 0.01257 0.00557 0.0000 0.7255 0.6966
-0.500 -0.0560 0.01256 0.00551 -0.0001 0.7213 0.7031
-0.250 -0.0280 0.01258 0.00552 0.0001 0.7178 0.7072
0.000 0.0000 0.01260 0.00558 0.0000 0.7121 0.7122
0.250 0.0280 0.01258 0.00552 -0.0001 0.7071 0.7178
0.500 0.0560 0.01256 0.00551 0.0000 0.7031 0.7213
0.750 0.0839 0.01257 0.00557 0.0000 0.6967 0.7255
1.000 0.1120 0.01253 0.00552 -0.0001 0.6911 0.7303
1.250 0.1400 0.01249 0.00550 -0.0001 0.6854 0.7341
1.500 0.1678 0.01246 0.00552 0.0000 0.6779 0.7375
1.750 0.1958 0.01240 0.00547 0.0001 0.6714 0.7414
2.000 0.2237 0.01236 0.00545 0.0000 0.6627 0.7457
2.250 0.2516 0.01230 0.00543 0.0000 0.6548 0.7490
2.500 0.2794 0.01225 0.00543 0.0001 0.6459 0.7522
2.750 0.3071 0.01222 0.00545 0.0002 0.6354 0.7557
3.000 0.3350 0.01217 0.00542 0.0002 0.6243 0.7595
3.250 0.3627 0.01212 0.00538 0.0002 0.6116 0.7629
3.500 0.3900 0.01208 0.00539 0.0004 0.5969 0.7656
3.750 0.4171 0.01207 0.00540 0.0006 0.5796 0.7685
4.000 0.4440 0.01208 0.00539 0.0008 0.5593 0.7718
4.250 0.4707 0.01214 0.00541 0.0010 0.5354 0.7754
4.500 0.4964 0.01226 0.00545 0.0014 0.5080 0.7782
4.750 0.5213 0.01244 0.00556 0.0019 0.4782 0.7809
5.000 0.5456 0.01269 0.00572 0.0024 0.4473 0.7841
5.250 0.5694 0.01299 0.00594 0.0029 0.4144 0.7875
5.500 0.5928 0.01335 0.00618 0.0034 0.3823 0.7910
5.750 0.6151 0.01373 0.00647 0.0041 0.3499 0.7938
6.000 0.6369 0.01414 0.00680 0.0048 0.3183 0.7970
6.250 0.6584 0.01458 0.00717 0.0056 0.2880 0.8006
6.500 0.6797 0.01505 0.00755 0.0063 0.2597 0.8043
6.750 0.7004 0.01552 0.00795 0.0070 0.2335 0.8077
7.000 0.7204 0.01599 0.00839 0.0080 0.2085 0.8112
7.250 0.7398 0.01651 0.00884 0.0089 0.1854 0.8153
7.500 0.7592 0.01704 0.00933 0.0098 0.1638 0.8196
7.750 0.7771 0.01760 0.00985 0.0110 0.1447 0.8235
8.000 0.7948 0.01814 0.01038 0.0121 0.1268 0.8280
8.250 0.8121 0.01872 0.01094 0.0133 0.1111 0.8333
8.500 0.8281 0.01931 0.01152 0.0147 0.0975 0.8384
8.750 0.8425 0.01991 0.01214 0.0163 0.0860 0.8440
9.000 0.8542 0.02054 0.01280 0.0182 0.0762 0.8510
9.250 0.8661 0.02118 0.01350 0.0202 0.0676 0.8587
9.500 0.8783 0.02192 0.01430 0.0218 0.0608 0.8682
10.000 0.9024 0.02357 0.01611 0.0248 0.0486 0.8959
10.250 0.9171 0.02460 0.01722 0.0252 0.0432 0.9237
10.500 0.9384 0.02568 0.01843 0.0242 0.0383 1.0000
10.750 0.9498 0.02684 0.01962 0.0250 0.0348 1.0000
11.000 0.9589 0.02818 0.02098 0.0259 0.0319 1.0000
11.250 0.9706 0.02934 0.02223 0.0266 0.0293 1.0000
11.500 0.9799 0.03073 0.02366 0.0273 0.0270 1.0000
11.750 0.9846 0.03248 0.02543 0.0282 0.0250 1.0000
12.000 0.9939 0.03391 0.02697 0.0288 0.0235 1.0000
12.250 1.0018 0.03548 0.02863 0.0294 0.0218 1.0000
12.500 1.0085 0.03718 0.03040 0.0299 0.0203 1.0000
12.750 1.0109 0.03930 0.03255 0.0303 0.0191 1.0000
13.000 1.0147 0.04139 0.03476 0.0307 0.0181 1.0000
13.250 1.0185 0.04353 0.03704 0.0309 0.0172 1.0000
13.500 1.0211 0.04585 0.03948 0.0310 0.0165 1.0000
13.750 1.0231 0.04830 0.04202 0.0308 0.0156 1.0000
14.000 1.0234 0.05102 0.04484 0.0305 0.0150 1.0000
14.250 1.0202 0.05427 0.04816 0.0298 0.0143 1.0000
14.500 1.0172 0.05766 0.05166 0.0290 0.0138 1.0000
14.750 1.0161 0.06101 0.05517 0.0280 0.0133 1.0000
15.000 1.0146 0.06459 0.05891 0.0267 0.0126 1.0000
15.250 1.0109 0.06860 0.06305 0.0251 0.0122 1.0000
15.500 1.0056 0.07297 0.06756 0.0232 0.0119 1.0000
15.750 0.9997 0.07767 0.07239 0.0209 0.0115 1.0000
16.000 0.9919 0.08283 0.07767 0.0183 0.0112 1.0000
16.250 0.9844 0.08806 0.08304 0.0157 0.0112 1.0000
16.500 0.9751 0.09381 0.08892 0.0126 0.0110 1.0000
16.750 0.9645 0.09999 0.09522 0.0092 0.0108 1.0000
17.000 0.9544 0.10620 0.10156 0.0057 0.0107 1.0000
17.250 0.9429 0.11288 0.10836 0.0020 0.0106 1.0000
17.500 0.9315 0.11970 0.11531 -0.0019 0.0105 1.0000
17.750 0.9191 0.12684 0.12255 -0.0060 0.0104 1.0000
18.000 0.9063 0.13431 0.13014 -0.0104 0.0103 1.0000
18.250 0.8927 0.14231 0.13827 -0.0151 0.0103 1.0000
18.500 0.8748 0.15175 0.14786 -0.0206 0.0103 1.0000
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