EPPLER 502 AIRFOIL (e502-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 502 AIRFOIL (e502-il) Reynolds number: 200,000 Max Cl/Cd: 58 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e502-il-200000-n5.txt Download as CSV file: xf-e502-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 502 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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5188 0.09040 0.08708 -0.0531 1.0000 0.0077
-12.500 -0.5678 0.07241 0.06893 -0.0643 1.0000 0.0074
-12.250 -0.5929 0.06553 0.06191 -0.0678 1.0000 0.0071
-12.000 -0.6164 0.05820 0.05429 -0.0723 0.9340 0.0070
-11.750 -0.6375 0.05093 0.04651 -0.0760 0.9005 0.0071
-11.500 -0.6532 0.04640 0.04155 -0.0757 0.8767 0.0070
-11.250 -0.6675 0.04268 0.03741 -0.0737 0.8603 0.0071
-11.000 -0.6747 0.03972 0.03407 -0.0714 0.8483 0.0071
-10.750 -0.6784 0.03699 0.03095 -0.0688 0.8387 0.0073
-10.500 -0.6770 0.03445 0.02803 -0.0664 0.8303 0.0074
-10.250 -0.6696 0.03233 0.02556 -0.0645 0.8236 0.0076
-10.000 -0.6574 0.03029 0.02313 -0.0629 0.8175 0.0082
-9.750 -0.6425 0.02876 0.02136 -0.0616 0.8126 0.0082
-9.500 -0.6268 0.02731 0.01972 -0.0604 0.8077 0.0088
-9.250 -0.6115 0.02652 0.01885 -0.0593 0.8028 0.0095
-9.000 -0.5948 0.02597 0.01816 -0.0581 0.7987 0.0109
-8.750 -0.5746 0.02496 0.01696 -0.0574 0.7945 0.0117
-8.500 -0.5554 0.02375 0.01559 -0.0564 0.7903 0.0126
-8.250 -0.5381 0.02287 0.01463 -0.0552 0.7865 0.0136
-8.000 -0.5199 0.02211 0.01377 -0.0540 0.7834 0.0153
-7.750 -0.5016 0.02133 0.01286 -0.0528 0.7797 0.0173
-7.500 -0.4841 0.02070 0.01224 -0.0517 0.7762 0.0207
-7.250 -0.4653 0.02016 0.01157 -0.0505 0.7730 0.0242
-7.000 -0.4492 0.01950 0.01091 -0.0490 0.7701 0.0289
-6.750 -0.4307 0.01906 0.01034 -0.0477 0.7670 0.0330
-6.500 -0.4161 0.01844 0.00974 -0.0459 0.7635 0.0381
-6.250 -0.3985 0.01807 0.00928 -0.0444 0.7606 0.0434
-6.000 -0.3841 0.01756 0.00876 -0.0423 0.7579 0.0492
-5.750 -0.3670 0.01719 0.00829 -0.0407 0.7556 0.0561
-5.500 -0.3506 0.01672 0.00786 -0.0390 0.7528 0.0675
-5.250 -0.3340 0.01626 0.00746 -0.0373 0.7497 0.0850
-5.000 -0.3187 0.01575 0.00706 -0.0355 0.7468 0.1164
-4.750 -0.3061 0.01511 0.00667 -0.0332 0.7443 0.1741
-4.500 -0.2975 0.01432 0.00626 -0.0303 0.7421 0.2633
-4.250 -0.2934 0.01339 0.00582 -0.0265 0.7399 0.3775
-4.000 -0.2953 0.01232 0.00566 -0.0212 0.7367 0.5490
-3.750 -0.2738 0.01266 0.00644 -0.0190 0.7341 0.6725
-3.500 -0.2509 0.01286 0.00652 -0.0179 0.7316 0.7015
-3.250 -0.2269 0.01313 0.00668 -0.0170 0.7295 0.7224
-3.000 -0.2013 0.01359 0.00708 -0.0159 0.7278 0.7422
-2.750 -0.1724 0.01427 0.00773 -0.0151 0.7261 0.7598
-2.500 -0.1460 0.01470 0.00813 -0.0143 0.7234 0.7718
-2.250 -0.1186 0.01491 0.00829 -0.0141 0.7208 0.7782
-2.000 -0.0966 0.01477 0.00803 -0.0134 0.7184 0.7830
-1.750 -0.0686 0.01475 0.00793 -0.0137 0.7164 0.7845
-1.500 -0.0409 0.01471 0.00782 -0.0138 0.7144 0.7860
-1.250 -0.0133 0.01467 0.00770 -0.0140 0.7126 0.7877
-1.000 0.0128 0.01464 0.00762 -0.0140 0.7103 0.7895
-0.750 0.0381 0.01461 0.00755 -0.0139 0.7077 0.7916
-0.500 0.0634 0.01455 0.00745 -0.0139 0.7051 0.7937
-0.250 0.0886 0.01447 0.00731 -0.0138 0.7027 0.7961
0.000 0.1152 0.01441 0.00720 -0.0139 0.7006 0.7978
0.250 0.1432 0.01439 0.00714 -0.0142 0.6989 0.7988
0.500 0.1705 0.01440 0.00713 -0.0144 0.6968 0.8000
0.750 0.1959 0.01444 0.00720 -0.0143 0.6936 0.8015
1.000 0.2221 0.01445 0.00722 -0.0144 0.6907 0.8029
1.250 0.2488 0.01444 0.00720 -0.0145 0.6881 0.8043
1.500 0.2761 0.01441 0.00716 -0.0147 0.6858 0.8057
1.750 0.3040 0.01438 0.00711 -0.0150 0.6838 0.8075
2.000 0.3283 0.01443 0.00720 -0.0148 0.6800 0.8095
2.250 0.3536 0.01443 0.00722 -0.0147 0.6761 0.8112
2.500 0.3808 0.01440 0.00722 -0.0149 0.6729 0.8123
2.750 0.4094 0.01435 0.00718 -0.0152 0.6701 0.8134
3.000 0.4344 0.01439 0.00729 -0.0150 0.6658 0.8146
3.250 0.4599 0.01439 0.00736 -0.0148 0.6609 0.8160
3.500 0.4878 0.01431 0.00731 -0.0150 0.6570 0.8175
3.750 0.5136 0.01430 0.00735 -0.0148 0.6522 0.8194
4.000 0.5383 0.01429 0.00741 -0.0145 0.6463 0.8212
4.250 0.5667 0.01416 0.00732 -0.0148 0.6416 0.8228
4.500 0.5898 0.01417 0.00743 -0.0142 0.6345 0.8247
4.750 0.6169 0.01406 0.00736 -0.0142 0.6284 0.8263
5.000 0.6404 0.01405 0.00749 -0.0136 0.6205 0.8277
5.250 0.6673 0.01392 0.00740 -0.0135 0.6130 0.8292
5.500 0.6896 0.01390 0.00751 -0.0126 0.6020 0.8310
5.750 0.7129 0.01386 0.00756 -0.0119 0.5904 0.8331
6.000 0.7358 0.01381 0.00761 -0.0112 0.5769 0.8355
6.250 0.7583 0.01377 0.00763 -0.0103 0.5604 0.8380
6.500 0.7798 0.01375 0.00764 -0.0093 0.5391 0.8405
6.750 0.7990 0.01379 0.00765 -0.0077 0.5080 0.8424
7.000 0.8126 0.01401 0.00770 -0.0051 0.4640 0.8449
7.250 0.8184 0.01450 0.00796 -0.0014 0.4165 0.8482
7.500 0.8193 0.01511 0.00838 0.0030 0.3746 0.8523
7.750 0.8170 0.01577 0.00892 0.0078 0.3384 0.8564
8.000 0.8162 0.01658 0.00962 0.0120 0.3048 0.8608
8.250 0.8153 0.01755 0.01046 0.0158 0.2709 0.8666
8.500 0.8165 0.01854 0.01136 0.0190 0.2393 0.8722
8.750 0.8191 0.01957 0.01231 0.0218 0.2104 0.8785
9.000 0.8230 0.02069 0.01333 0.0242 0.1816 0.8852
9.250 0.8289 0.02180 0.01438 0.0261 0.1558 0.8929
9.500 0.8360 0.02296 0.01548 0.0277 0.1321 0.9020
9.750 0.8446 0.02418 0.01664 0.0289 0.1078 0.9136
10.000 0.8582 0.02544 0.01790 0.0290 0.0868 0.9282
10.250 0.8767 0.02687 0.01931 0.0278 0.0680 0.9476
10.500 0.8962 0.02829 0.02072 0.0263 0.0526 1.0000
10.750 0.9038 0.02959 0.02197 0.0275 0.0434 1.0000
11.000 0.9122 0.03089 0.02327 0.0285 0.0357 1.0000
11.250 0.9206 0.03220 0.02461 0.0296 0.0301 1.0000
11.500 0.9266 0.03374 0.02613 0.0307 0.0252 1.0000
11.750 0.9349 0.03513 0.02760 0.0316 0.0210 1.0000
12.000 0.9409 0.03674 0.02925 0.0326 0.0185 1.0000
12.250 0.9462 0.03844 0.03103 0.0336 0.0162 1.0000
12.500 0.9533 0.04004 0.03271 0.0343 0.0140 1.0000
12.750 0.9570 0.04197 0.03468 0.0351 0.0124 1.0000
13.000 0.9605 0.04400 0.03681 0.0358 0.0117 1.0000
13.250 0.9643 0.04606 0.03900 0.0365 0.0109 1.0000
13.500 0.9676 0.04822 0.04127 0.0370 0.0101 1.0000
13.750 0.9706 0.05048 0.04362 0.0374 0.0094 1.0000
14.000 0.9703 0.05313 0.04632 0.0376 0.0082 1.0000
14.250 0.9733 0.05555 0.04888 0.0378 0.0078 1.0000
14.500 0.9716 0.05850 0.05192 0.0379 0.0082 1.0000
14.750 0.9765 0.06086 0.05446 0.0378 0.0074 1.0000
15.000 0.9793 0.06352 0.05724 0.0374 0.0066 1.0000
15.250 0.9776 0.06679 0.06068 0.0370 0.0065 1.0000
15.500 0.9770 0.07003 0.06403 0.0363 0.0061 1.0000
15.750 0.9744 0.07362 0.06776 0.0355 0.0060 1.0000
16.000 0.9714 0.07739 0.07166 0.0344 0.0059 1.0000
16.250 0.9660 0.08164 0.07604 0.0331 0.0058 1.0000
16.500 0.9569 0.08657 0.08110 0.0314 0.0056 1.0000
16.750 0.9517 0.09106 0.08573 0.0297 0.0056 1.0000
17.000 0.9429 0.09638 0.09124 0.0276 0.0054 1.0000
17.250 0.9351 0.10164 0.09667 0.0253 0.0054 1.0000
17.500 0.9269 0.10717 0.10235 0.0226 0.0054 1.0000
17.750 0.9179 0.11294 0.10826 0.0197 0.0055 1.0000
18.000 0.9041 0.12007 0.11560 0.0160 0.0053 1.0000
18.250 0.8951 0.12626 0.12192 0.0126 0.0054 1.0000
18.500 0.8797 0.13423 0.13007 0.0081 0.0053 1.0000
18.750 0.8676 0.14157 0.13755 0.0040 0.0054 1.0000
19.000 0.8525 0.15010 0.14622 -0.0009 0.0054 1.0000
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Polar data table (+)
Polar graphs
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