E203 (13.64%) (e203-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: E203 (13.64%) (e203-il) Reynolds number: 500,000 Max Cl/Cd: 109.38 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e203-il-500000.txt Download as CSV file: xf-e203-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: E203 (13.64%)
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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.5542 0.08998 0.08758 -0.0511 1.0000 0.0183
-12.750 -0.5905 0.07714 0.07457 -0.0591 1.0000 0.0171
-12.500 -0.6210 0.06794 0.06524 -0.0656 1.0000 0.0171
-12.250 -0.6491 0.06041 0.05760 -0.0702 1.0000 0.0166
-12.000 -0.6733 0.05423 0.05128 -0.0742 1.0000 0.0166
-11.750 -0.6952 0.04915 0.04607 -0.0767 1.0000 0.0163
-11.500 -0.7161 0.04514 0.04191 -0.0779 1.0000 0.0164
-11.250 -0.7382 0.04201 0.03864 -0.0770 1.0000 0.0163
-11.000 -0.7647 0.04000 0.03652 -0.0730 1.0000 0.0162
-10.750 -0.7840 0.03821 0.03460 -0.0684 1.0000 0.0162
-10.500 -0.7986 0.03593 0.03213 -0.0644 1.0000 0.0163
-10.250 -0.8017 0.03363 0.02960 -0.0620 0.9994 0.0163
-10.000 -0.7774 0.03038 0.02597 -0.0649 0.9956 0.0166
-9.750 -0.7500 0.02794 0.02322 -0.0672 0.9921 0.0169
-9.500 -0.7192 0.02659 0.02162 -0.0693 0.9881 0.0174
-9.250 -0.6910 0.02366 0.01839 -0.0714 0.9851 0.0180
-9.000 -0.6608 0.02162 0.01622 -0.0733 0.9821 0.0184
-8.750 -0.6319 0.02028 0.01481 -0.0744 0.9768 0.0190
-8.500 -0.5982 0.01912 0.01356 -0.0764 0.9736 0.0195
-8.250 -0.5625 0.01799 0.01234 -0.0787 0.9713 0.0202
-8.000 -0.5349 0.01709 0.01137 -0.0792 0.9639 0.0209
-7.750 -0.5002 0.01621 0.01041 -0.0811 0.9599 0.0218
-7.500 -0.4677 0.01551 0.00963 -0.0823 0.9541 0.0224
-7.250 -0.4408 0.01428 0.00831 -0.0828 0.9450 0.0234
-7.000 -0.4131 0.01341 0.00739 -0.0832 0.9341 0.0245
-6.750 -0.3819 0.01278 0.00670 -0.0841 0.9235 0.0258
-6.500 -0.3506 0.01223 0.00606 -0.0850 0.9107 0.0276
-6.250 -0.3213 0.01169 0.00541 -0.0854 0.8949 0.0301
-6.000 -0.2940 0.01124 0.00489 -0.0854 0.8773 0.0350
-5.750 -0.2689 0.01066 0.00431 -0.0850 0.8593 0.0542
-5.500 -0.2446 0.01012 0.00389 -0.0846 0.8421 0.0958
-5.250 -0.2198 0.00973 0.00358 -0.0843 0.8263 0.1317
-5.000 -0.1947 0.00940 0.00331 -0.0839 0.8117 0.1696
-4.750 -0.1697 0.00904 0.00305 -0.0836 0.7980 0.2148
-4.500 -0.1448 0.00867 0.00282 -0.0833 0.7854 0.2711
-4.250 -0.1194 0.00836 0.00266 -0.0830 0.7740 0.3251
-4.000 -0.0932 0.00821 0.00256 -0.0828 0.7633 0.3740
-3.750 -0.0663 0.00814 0.00252 -0.0826 0.7527 0.4080
-3.500 -0.0390 0.00813 0.00249 -0.0825 0.7435 0.4328
-3.250 -0.0115 0.00814 0.00243 -0.0824 0.7345 0.4484
-3.000 0.0161 0.00813 0.00239 -0.0823 0.7258 0.4627
-2.750 0.0436 0.00816 0.00236 -0.0822 0.7180 0.4767
-2.500 0.0714 0.00815 0.00232 -0.0821 0.7101 0.4871
-2.250 0.0993 0.00820 0.00227 -0.0821 0.7029 0.4971
-2.000 0.1270 0.00817 0.00226 -0.0820 0.6955 0.5064
-1.750 0.1549 0.00819 0.00222 -0.0820 0.6889 0.5155
-1.500 0.1828 0.00820 0.00221 -0.0820 0.6823 0.5247
-1.250 0.2106 0.00819 0.00219 -0.0820 0.6756 0.5333
-1.000 0.2386 0.00824 0.00218 -0.0820 0.6697 0.5424
-0.750 0.2664 0.00821 0.00218 -0.0820 0.6634 0.5510
-0.500 0.2944 0.00826 0.00217 -0.0820 0.6576 0.5600
-0.250 0.3221 0.00824 0.00220 -0.0820 0.6517 0.5690
0.000 0.3500 0.00825 0.00221 -0.0819 0.6459 0.5787
0.250 0.3779 0.00830 0.00223 -0.0820 0.6406 0.5896
0.500 0.4056 0.00827 0.00227 -0.0819 0.6346 0.6001
0.750 0.4333 0.00829 0.00229 -0.0819 0.6292 0.6110
1.000 0.4612 0.00832 0.00234 -0.0819 0.6240 0.6233
1.500 0.5164 0.00834 0.00244 -0.0818 0.6131 0.6515
1.750 0.5438 0.00834 0.00252 -0.0817 0.6077 0.6683
2.000 0.5709 0.00832 0.00259 -0.0816 0.6020 0.6872
2.250 0.5981 0.00836 0.00266 -0.0814 0.5967 0.7094
2.500 0.6246 0.00832 0.00276 -0.0812 0.5906 0.7353
2.750 0.6507 0.00830 0.00284 -0.0807 0.5840 0.7652
3.000 0.6762 0.00828 0.00294 -0.0802 0.5775 0.7991
3.250 0.7006 0.00823 0.00303 -0.0793 0.5706 0.8387
3.500 0.7234 0.00821 0.00313 -0.0780 0.5644 0.8867
3.750 0.7504 0.00815 0.00322 -0.0775 0.5568 0.9442
4.000 0.7934 0.00821 0.00328 -0.0808 0.5484 0.9922
4.250 0.8217 0.00828 0.00336 -0.0810 0.5399 1.0000
4.500 0.8475 0.00839 0.00347 -0.0807 0.5318 1.0000
4.750 0.8731 0.00850 0.00356 -0.0803 0.5230 1.0000
5.000 0.8989 0.00859 0.00368 -0.0799 0.5134 1.0000
5.250 0.9242 0.00872 0.00381 -0.0795 0.5032 1.0000
5.500 0.9492 0.00886 0.00393 -0.0790 0.4918 1.0000
5.750 0.9744 0.00899 0.00408 -0.0785 0.4789 1.0000
6.000 0.9988 0.00915 0.00423 -0.0779 0.4640 1.0000
6.250 1.0227 0.00935 0.00442 -0.0772 0.4475 1.0000
6.500 1.0464 0.00957 0.00462 -0.0765 0.4285 1.0000
6.750 1.0678 0.00990 0.00486 -0.0754 0.4001 1.0000
7.000 1.0867 0.01038 0.00517 -0.0739 0.3602 1.0000
7.250 1.1012 0.01113 0.00565 -0.0718 0.3039 1.0000
7.500 1.1133 0.01205 0.00625 -0.0694 0.2475 1.0000
7.750 1.1262 0.01291 0.00687 -0.0671 0.2023 1.0000
8.000 1.1392 0.01373 0.00748 -0.0648 0.1644 1.0000
8.250 1.1519 0.01451 0.00809 -0.0626 0.1333 1.0000
8.500 1.1635 0.01523 0.00869 -0.0600 0.1095 1.0000
8.750 1.1733 0.01597 0.00931 -0.0572 0.0896 1.0000
9.000 1.1841 0.01667 0.00995 -0.0546 0.0742 1.0000
9.250 1.1947 0.01741 0.01063 -0.0521 0.0607 1.0000
9.500 1.2037 0.01824 0.01141 -0.0494 0.0473 1.0000
9.750 1.2091 0.01931 0.01238 -0.0464 0.0333 1.0000
10.000 1.2122 0.02055 0.01356 -0.0433 0.0224 1.0000
10.250 1.2185 0.02169 0.01474 -0.0408 0.0184 1.0000
10.750 1.2306 0.02419 0.01734 -0.0363 0.0147 1.0000
11.000 1.2386 0.02541 0.01862 -0.0346 0.0136 1.0000
11.250 1.2428 0.02698 0.02024 -0.0327 0.0127 1.0000
11.500 1.2415 0.02908 0.02242 -0.0307 0.0121 1.0000
11.750 1.2485 0.03061 0.02404 -0.0294 0.0117 1.0000
12.000 1.2531 0.03241 0.02593 -0.0282 0.0114 1.0000
12.250 1.2570 0.03434 0.02797 -0.0271 0.0111 1.0000
12.500 1.2600 0.03642 0.03013 -0.0261 0.0109 1.0000
12.750 1.2639 0.03849 0.03228 -0.0253 0.0105 1.0000
13.000 1.2661 0.04079 0.03466 -0.0246 0.0102 1.0000
13.250 1.2676 0.04320 0.03715 -0.0240 0.0100 1.0000
13.500 1.2691 0.04569 0.03972 -0.0235 0.0099 1.0000
13.750 1.2683 0.04849 0.04260 -0.0231 0.0097 1.0000
14.000 1.2637 0.05177 0.04596 -0.0227 0.0094 1.0000
14.250 1.2674 0.05425 0.04852 -0.0225 0.0095 1.0000
14.500 1.2614 0.05783 0.05221 -0.0221 0.0092 1.0000
14.750 1.2624 0.06075 0.05523 -0.0220 0.0091 1.0000
15.000 1.2652 0.06356 0.05817 -0.0222 0.0090 1.0000
15.250 1.2666 0.06659 0.06131 -0.0224 0.0089 1.0000
15.500 1.2678 0.06973 0.06457 -0.0228 0.0089 1.0000
15.750 1.2685 0.07298 0.06794 -0.0232 0.0089 1.0000
16.000 1.2675 0.07662 0.07173 -0.0240 0.0087 1.0000
16.250 1.2664 0.08037 0.07561 -0.0249 0.0086 1.0000
16.500 1.2635 0.08443 0.07982 -0.0260 0.0085 1.0000
16.750 1.2605 0.08862 0.08415 -0.0275 0.0084 1.0000
17.000 1.2559 0.09319 0.08886 -0.0290 0.0083 1.0000
17.250 1.2513 0.09788 0.09369 -0.0310 0.0083 1.0000
17.500 1.2430 0.10329 0.09927 -0.0331 0.0083 1.0000
17.750 1.2353 0.10877 0.10490 -0.0357 0.0082 1.0000
18.000 1.2252 0.11484 0.11115 -0.0387 0.0081 1.0000
18.250 1.2153 0.12105 0.11751 -0.0419 0.0082 1.0000
18.500 1.2036 0.12777 0.12440 -0.0457 0.0081 1.0000
18.750 1.1903 0.13504 0.13184 -0.0499 0.0082 1.0000
19.000 1.1733 0.14344 0.14043 -0.0550 0.0082 1.0000
19.250 1.1571 0.15196 0.14912 -0.0604 0.0083 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E203 (13.64%) (e203-il)