EPPLER 521 AIRFOIL (e521-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 521 AIRFOIL (e521-il) Reynolds number: 500,000 Max Cl/Cd: 58.73 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e521-il-500000.txt Download as CSV file: xf-e521-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 521 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.9152 0.13310 0.13026 0.0081 1.0000 0.0061
-17.750 -0.9310 0.12467 0.12169 0.0031 1.0000 0.0061
-17.500 -0.9443 0.11702 0.11390 -0.0014 1.0000 0.0060
-17.250 -0.9617 0.10877 0.10551 -0.0061 1.0000 0.0060
-17.000 -0.9759 0.10148 0.09808 -0.0103 1.0000 0.0060
-16.750 -0.9789 0.09636 0.09287 -0.0134 1.0000 0.0059
-16.500 -1.0013 0.08804 0.08437 -0.0179 1.0000 0.0060
-16.250 -1.0090 0.08250 0.07870 -0.0210 1.0000 0.0059
-16.000 -1.0152 0.07738 0.07346 -0.0238 1.0000 0.0059
-15.750 -1.0364 0.07021 0.06611 -0.0273 1.0000 0.0061
-15.500 -1.0478 0.06484 0.06059 -0.0297 1.0000 0.0062
-15.250 -1.0556 0.06021 0.05583 -0.0317 1.0000 0.0062
-15.000 -1.0649 0.05564 0.05114 -0.0334 1.0000 0.0064
-14.750 -1.0684 0.05206 0.04741 -0.0343 1.0000 0.0062
-14.500 -1.0735 0.04851 0.04374 -0.0352 1.0000 0.0063
-14.250 -1.0757 0.04551 0.04067 -0.0357 1.0000 0.0066
-14.000 -1.0775 0.04267 0.03771 -0.0358 1.0000 0.0068
-13.750 -1.0803 0.03987 0.03478 -0.0355 1.0000 0.0067
-13.500 -1.0753 0.03796 0.03281 -0.0353 1.0000 0.0072
-13.250 -1.0719 0.03595 0.03070 -0.0348 1.0000 0.0076
-13.000 -1.0704 0.03383 0.02847 -0.0339 1.0000 0.0078
-12.750 -1.0659 0.03205 0.02658 -0.0330 1.0000 0.0080
-12.500 -1.0585 0.03056 0.02498 -0.0321 1.0000 0.0083
-12.250 -1.0612 0.02832 0.02263 -0.0304 1.0000 0.0088
-12.000 -1.0603 0.02645 0.02070 -0.0287 1.0000 0.0094
-11.750 -1.0487 0.02542 0.01961 -0.0278 1.0000 0.0104
-11.500 -1.0397 0.02421 0.01833 -0.0264 1.0000 0.0111
-11.250 -1.0257 0.02336 0.01740 -0.0254 1.0000 0.0119
-11.000 -1.0237 0.02173 0.01572 -0.0233 1.0000 0.0136
-10.750 -1.0097 0.02090 0.01487 -0.0222 1.0000 0.0152
-10.500 -0.9920 0.02030 0.01421 -0.0215 1.0000 0.0166
-10.250 -0.9734 0.01901 0.01290 -0.0219 0.9622 0.0198
-10.000 -0.9442 0.01859 0.01239 -0.0230 0.9389 0.0226
-9.750 -0.9373 0.01776 0.01144 -0.0201 0.9199 0.0257
-9.500 -0.9237 0.01736 0.01098 -0.0180 0.9098 0.0288
-9.250 -0.9080 0.01687 0.01040 -0.0163 0.9017 0.0320
-9.000 -0.8934 0.01625 0.00977 -0.0145 0.8952 0.0373
-8.750 -0.8749 0.01574 0.00921 -0.0132 0.8895 0.0429
-8.500 -0.8563 0.01524 0.00871 -0.0120 0.8846 0.0508
-8.250 -0.8377 0.01470 0.00819 -0.0108 0.8802 0.0616
-8.000 -0.8174 0.01420 0.00773 -0.0099 0.8757 0.0744
-7.750 -0.7965 0.01374 0.00729 -0.0090 0.8718 0.0888
-7.500 -0.7755 0.01331 0.00690 -0.0081 0.8684 0.1046
-7.250 -0.7537 0.01287 0.00653 -0.0074 0.8648 0.1228
-7.000 -0.7310 0.01247 0.00619 -0.0069 0.8611 0.1426
-6.750 -0.7085 0.01206 0.00586 -0.0062 0.8579 0.1637
-6.250 -0.6625 0.01134 0.00527 -0.0051 0.8519 0.2142
-5.750 -0.6153 0.01057 0.00474 -0.0042 0.8455 0.2742
-5.500 -0.5918 0.01020 0.00449 -0.0037 0.8425 0.3076
-5.250 -0.5680 0.00986 0.00426 -0.0032 0.8397 0.3428
-5.000 -0.5437 0.00954 0.00406 -0.0028 0.8370 0.3784
-4.750 -0.5190 0.00921 0.00386 -0.0025 0.8337 0.4157
-4.500 -0.4944 0.00889 0.00368 -0.0021 0.8306 0.4532
-4.000 -0.4447 0.00837 0.00338 -0.0013 0.8249 0.5291
-3.750 -0.4191 0.00815 0.00330 -0.0010 0.8217 0.5676
-3.500 -0.3928 0.00799 0.00325 -0.0007 0.8181 0.6017
-3.250 -0.3660 0.00790 0.00322 -0.0005 0.8147 0.6295
-3.000 -0.3387 0.00787 0.00321 -0.0003 0.8116 0.6518
-2.750 -0.3111 0.00789 0.00324 -0.0001 0.8085 0.6690
-2.500 -0.2829 0.00790 0.00326 -0.0002 0.8045 0.6834
-2.250 -0.2548 0.00793 0.00327 -0.0002 0.8006 0.6960
-2.000 -0.2267 0.00797 0.00327 -0.0001 0.7971 0.7071
-1.750 -0.1985 0.00803 0.00333 0.0000 0.7935 0.7155
-1.500 -0.1701 0.00806 0.00334 -0.0001 0.7888 0.7242
-1.250 -0.1418 0.00810 0.00337 -0.0001 0.7847 0.7313
-1.000 -0.1135 0.00814 0.00336 0.0000 0.7810 0.7384
-0.750 -0.0851 0.00817 0.00343 0.0000 0.7761 0.7443
-0.500 -0.0567 0.00820 0.00341 -0.0001 0.7713 0.7513
-0.250 -0.0284 0.00820 0.00342 0.0000 0.7672 0.7561
0.000 0.0000 0.00822 0.00346 0.0000 0.7618 0.7618
0.250 0.0284 0.00820 0.00342 0.0000 0.7561 0.7672
0.500 0.0567 0.00820 0.00341 0.0001 0.7513 0.7713
0.750 0.0851 0.00817 0.00343 0.0000 0.7443 0.7762
1.000 0.1136 0.00814 0.00336 0.0000 0.7384 0.7810
1.250 0.1418 0.00810 0.00337 0.0001 0.7312 0.7847
1.500 0.1701 0.00806 0.00334 0.0001 0.7242 0.7889
1.750 0.1985 0.00803 0.00333 0.0000 0.7156 0.7935
2.000 0.2267 0.00797 0.00327 0.0001 0.7070 0.7971
2.250 0.2548 0.00793 0.00327 0.0002 0.6960 0.8006
2.500 0.2829 0.00790 0.00326 0.0002 0.6835 0.8045
2.750 0.3111 0.00789 0.00324 0.0001 0.6690 0.8085
3.000 0.3387 0.00787 0.00321 0.0003 0.6519 0.8116
3.250 0.3660 0.00790 0.00322 0.0005 0.6295 0.8147
3.500 0.3928 0.00799 0.00325 0.0007 0.6018 0.8181
3.750 0.4191 0.00815 0.00330 0.0009 0.5676 0.8217
4.000 0.4447 0.00837 0.00338 0.0013 0.5287 0.8249
4.500 0.4944 0.00889 0.00368 0.0021 0.4534 0.8306
4.750 0.5190 0.00921 0.00386 0.0025 0.4156 0.8338
5.000 0.5437 0.00954 0.00406 0.0028 0.3782 0.8370
5.250 0.5679 0.00986 0.00426 0.0032 0.3428 0.8397
5.500 0.5917 0.01019 0.00449 0.0037 0.3077 0.8425
5.750 0.6152 0.01056 0.00474 0.0042 0.2743 0.8455
6.250 0.6624 0.01133 0.00527 0.0051 0.2141 0.8519
6.500 0.6853 0.01171 0.00555 0.0057 0.1869 0.8549
6.750 0.7083 0.01206 0.00586 0.0063 0.1638 0.8579
7.000 0.7308 0.01247 0.00619 0.0069 0.1427 0.8612
7.250 0.7535 0.01286 0.00653 0.0075 0.1228 0.8649
7.500 0.7753 0.01331 0.00690 0.0082 0.1044 0.8684
7.750 0.7963 0.01374 0.00729 0.0090 0.0888 0.8718
8.000 0.8171 0.01419 0.00773 0.0099 0.0745 0.8758
8.250 0.8374 0.01469 0.00819 0.0108 0.0617 0.8803
8.500 0.8560 0.01524 0.00870 0.0121 0.0507 0.8847
8.750 0.8744 0.01574 0.00921 0.0133 0.0429 0.8896
9.000 0.8930 0.01625 0.00977 0.0145 0.0372 0.8953
9.250 0.9075 0.01688 0.01041 0.0164 0.0319 0.9018
9.500 0.9233 0.01735 0.01097 0.0181 0.0288 0.9099
9.750 0.9369 0.01774 0.01142 0.0202 0.0257 0.9201
10.000 0.9438 0.01858 0.01238 0.0231 0.0227 0.9394
10.250 0.9728 0.01909 0.01299 0.0219 0.0200 0.9635
10.500 0.9933 0.02021 0.01412 0.0214 0.0169 1.0000
10.750 1.0092 0.02092 0.01489 0.0223 0.0152 1.0000
11.000 1.0236 0.02171 0.01570 0.0233 0.0136 1.0000
11.250 1.0264 0.02329 0.01732 0.0254 0.0119 1.0000
11.500 1.0370 0.02437 0.01850 0.0267 0.0114 1.0000
11.750 1.0490 0.02538 0.01957 0.0278 0.0103 1.0000
12.000 1.0591 0.02652 0.02077 0.0289 0.0095 1.0000
12.250 1.0632 0.02814 0.02245 0.0303 0.0089 1.0000
12.500 1.0595 0.03044 0.02485 0.0320 0.0085 1.0000
12.750 1.0680 0.03186 0.02639 0.0329 0.0079 1.0000
13.000 1.0706 0.03380 0.02843 0.0339 0.0078 1.0000
13.250 1.0750 0.03565 0.03038 0.0346 0.0073 1.0000
13.500 1.0770 0.03779 0.03262 0.0352 0.0071 1.0000
13.750 1.0774 0.04017 0.03511 0.0356 0.0069 1.0000
14.000 1.0759 0.04284 0.03790 0.0358 0.0069 1.0000
14.250 1.0768 0.04539 0.04054 0.0356 0.0066 1.0000
14.500 1.0735 0.04852 0.04377 0.0352 0.0064 1.0000
14.750 1.0697 0.05192 0.04728 0.0344 0.0063 1.0000
15.000 1.0640 0.05578 0.05126 0.0332 0.0062 1.0000
15.250 1.0541 0.06043 0.05605 0.0316 0.0061 1.0000
15.500 1.0505 0.06447 0.06022 0.0298 0.0062 1.0000
15.750 1.0388 0.06989 0.06577 0.0273 0.0061 1.0000
16.000 1.0252 0.07585 0.07189 0.0244 0.0060 1.0000
16.250 1.0184 0.08106 0.07723 0.0216 0.0061 1.0000
16.500 1.0071 0.08712 0.08343 0.0183 0.0061 1.0000
16.750 0.9857 0.09520 0.09168 0.0139 0.0059 1.0000
17.000 0.9784 0.10108 0.09768 0.0105 0.0060 1.0000
17.250 0.9642 0.10841 0.10515 0.0062 0.0060 1.0000
17.500 0.9493 0.11610 0.11297 0.0018 0.0061 1.0000
17.750 0.9325 0.12450 0.12151 -0.0031 0.0061 1.0000
18.000 0.9141 0.13363 0.13082 -0.0085 0.0062 1.0000
18.250 0.8888 0.14486 0.14224 -0.0150 0.0063 1.0000
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