E230 (9.96%) (e230-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E230 (9.96%) (e230-il) Reynolds number: 200,000 Max Cl/Cd: 38.7 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e230-il-200000-n5.txt Download as CSV file: xf-e230-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E230 (9.96%)
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 -0.8474 0.11284 0.10950 0.0344 1.0000 0.0113
-12.750 -0.8805 0.09823 0.09482 0.0256 1.0000 0.0109
-12.500 -0.9093 0.08594 0.08238 0.0170 1.0000 0.0106
-12.250 -0.9357 0.07564 0.07189 0.0092 1.0000 0.0104
-12.000 -0.9593 0.06742 0.06347 0.0033 1.0000 0.0102
-11.750 -0.9767 0.06160 0.05745 -0.0003 1.0000 0.0103
-11.500 -0.9956 0.05639 0.05200 -0.0022 1.0000 0.0102
-11.250 -1.0122 0.05221 0.04758 -0.0024 1.0000 0.0102
-11.000 -1.0254 0.04880 0.04392 -0.0011 1.0000 0.0103
-10.750 -1.0357 0.04591 0.04078 0.0011 1.0000 0.0104
-10.500 -1.0429 0.04319 0.03779 0.0040 1.0000 0.0105
-10.250 -1.0449 0.04051 0.03479 0.0067 1.0000 0.0106
-10.000 -1.0410 0.03787 0.03182 0.0088 1.0000 0.0106
-9.750 -1.0328 0.03542 0.02905 0.0107 1.0000 0.0107
-9.500 -1.0211 0.03321 0.02655 0.0124 1.0000 0.0107
-9.250 -1.0068 0.03115 0.02424 0.0138 1.0000 0.0109
-9.000 -0.9904 0.02934 0.02217 0.0152 1.0000 0.0110
-8.750 -0.9729 0.02767 0.02031 0.0164 1.0000 0.0112
-8.500 -0.9546 0.02616 0.01863 0.0176 1.0000 0.0114
-8.250 -0.9357 0.02480 0.01712 0.0188 1.0000 0.0117
-8.000 -0.9164 0.02357 0.01576 0.0199 1.0000 0.0119
-7.750 -0.8980 0.02228 0.01437 0.0211 1.0000 0.0122
-7.500 -0.8793 0.02108 0.01307 0.0223 1.0000 0.0126
-7.250 -0.8588 0.02012 0.01203 0.0233 1.0000 0.0133
-7.000 -0.8370 0.01931 0.01113 0.0241 1.0000 0.0145
-6.750 -0.8147 0.01855 0.01026 0.0249 1.0000 0.0156
-6.500 -0.7924 0.01774 0.00935 0.0258 1.0000 0.0167
-6.250 -0.7696 0.01699 0.00852 0.0265 1.0000 0.0183
-6.000 -0.7460 0.01633 0.00778 0.0272 1.0000 0.0212
-5.750 -0.7233 0.01556 0.00705 0.0280 1.0000 0.0309
-5.500 -0.7013 0.01473 0.00639 0.0288 1.0000 0.0605
-5.250 -0.6796 0.01389 0.00585 0.0295 1.0000 0.1085
-5.000 -0.6569 0.01324 0.00541 0.0301 1.0000 0.1517
-4.750 -0.6336 0.01271 0.00504 0.0307 1.0000 0.1905
-4.500 -0.6116 0.01211 0.00471 0.0314 1.0000 0.2442
-4.250 -0.5896 0.01161 0.00443 0.0322 1.0000 0.2945
-4.000 -0.5644 0.01119 0.00418 0.0324 0.9899 0.3390
-3.500 -0.4992 0.01054 0.00376 0.0300 0.9570 0.4195
-3.250 -0.4707 0.01027 0.00358 0.0299 0.9416 0.4582
-3.000 -0.4452 0.01004 0.00345 0.0305 0.9259 0.4959
-2.750 -0.4213 0.00983 0.00333 0.0315 0.9106 0.5322
-2.500 -0.3983 0.00962 0.00322 0.0328 0.8956 0.5679
-2.250 -0.3754 0.00944 0.00312 0.0341 0.8808 0.6034
-2.000 -0.3526 0.00926 0.00304 0.0355 0.8663 0.6389
-1.750 -0.3293 0.00909 0.00297 0.0368 0.8519 0.6748
-1.500 -0.3053 0.00895 0.00289 0.0380 0.8375 0.7097
-1.250 -0.2802 0.00883 0.00285 0.0390 0.8229 0.7432
-1.000 -0.2538 0.00874 0.00282 0.0398 0.8081 0.7752
-0.750 -0.2256 0.00869 0.00281 0.0402 0.7928 0.8051
-0.500 -0.1953 0.00868 0.00281 0.0401 0.7769 0.8320
-0.250 -0.1628 0.00871 0.00283 0.0396 0.7601 0.8552
0.000 -0.1287 0.00878 0.00286 0.0387 0.7426 0.8748
0.250 -0.0934 0.00887 0.00291 0.0375 0.7244 0.8909
0.500 -0.0585 0.00898 0.00296 0.0364 0.7048 0.9047
0.750 -0.0248 0.00909 0.00302 0.0355 0.6843 0.9174
1.000 0.0119 0.00922 0.00307 0.0339 0.6628 0.9265
1.250 0.0463 0.00936 0.00314 0.0327 0.6396 0.9358
1.500 0.0775 0.00951 0.00322 0.0323 0.6160 0.9459
1.750 0.1141 0.00967 0.00330 0.0306 0.5895 0.9522
2.000 0.1462 0.00983 0.00338 0.0298 0.5626 0.9607
2.250 0.1820 0.00999 0.00347 0.0282 0.5331 0.9668
2.500 0.2150 0.01017 0.00356 0.0271 0.5034 0.9738
2.750 0.2509 0.01034 0.00364 0.0253 0.4705 0.9792
3.000 0.2846 0.01054 0.00377 0.0240 0.4362 0.9851
3.250 0.3214 0.01072 0.00386 0.0219 0.4000 0.9895
3.500 0.3565 0.01096 0.00399 0.0202 0.3619 0.9943
3.750 0.3926 0.01121 0.00413 0.0181 0.3183 0.9982
4.000 0.4223 0.01155 0.00429 0.0173 0.2692 1.0000
4.250 0.4461 0.01197 0.00449 0.0176 0.2163 1.0000
4.500 0.4698 0.01240 0.00475 0.0180 0.1725 1.0000
4.750 0.4935 0.01280 0.00505 0.0185 0.1407 1.0000
5.000 0.5167 0.01335 0.00540 0.0189 0.1002 1.0000
5.250 0.5395 0.01396 0.00582 0.0194 0.0659 1.0000
5.500 0.5622 0.01458 0.00635 0.0200 0.0401 1.0000
5.750 0.5847 0.01525 0.00697 0.0207 0.0272 1.0000
6.000 0.6073 0.01585 0.00763 0.0215 0.0232 1.0000
6.250 0.6294 0.01649 0.00832 0.0223 0.0211 1.0000
6.500 0.6510 0.01722 0.00914 0.0231 0.0198 1.0000
6.750 0.6724 0.01789 0.00994 0.0241 0.0184 1.0000
7.000 0.6932 0.01860 0.01073 0.0250 0.0172 1.0000
7.250 0.7132 0.01943 0.01164 0.0260 0.0163 1.0000
7.500 0.7318 0.02046 0.01274 0.0271 0.0157 1.0000
7.750 0.7490 0.02169 0.01404 0.0285 0.0153 1.0000
8.000 0.7672 0.02276 0.01523 0.0298 0.0150 1.0000
8.250 0.7848 0.02393 0.01656 0.0311 0.0148 1.0000
8.500 0.8016 0.02524 0.01802 0.0325 0.0145 1.0000
8.750 0.8178 0.02666 0.01961 0.0340 0.0143 1.0000
9.000 0.8329 0.02823 0.02137 0.0355 0.0141 1.0000
9.250 0.8464 0.03002 0.02339 0.0370 0.0139 1.0000
9.500 0.8579 0.03195 0.02556 0.0387 0.0138 1.0000
9.750 0.8672 0.03395 0.02785 0.0404 0.0136 1.0000
10.000 0.8736 0.03602 0.03018 0.0422 0.0133 1.0000
10.250 0.8772 0.03812 0.03252 0.0441 0.0130 1.0000
10.500 0.8783 0.04011 0.03469 0.0460 0.0126 1.0000
10.750 0.8705 0.04255 0.03736 0.0484 0.0126 1.0000
11.000 0.8576 0.04513 0.04014 0.0504 0.0126 1.0000
11.250 0.8476 0.04793 0.04309 0.0507 0.0124 1.0000
11.500 0.8339 0.05181 0.04715 0.0495 0.0123 1.0000
11.750 0.8177 0.05680 0.05235 0.0467 0.0123 1.0000
12.000 0.7929 0.06427 0.06005 0.0413 0.0125 1.0000
12.250 0.7522 0.07667 0.07273 0.0318 0.0130 1.0000
12.500 0.6906 0.09683 0.09304 0.0189 0.0140 1.0000
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Polar data table (+)
Polar graphs
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