E193 (10.22%) (e193-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E193 (10.22%) (e193-il) Reynolds number: 200,000 Max Cl/Cd: 80.33 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e193-il-200000-n5.txt Download as CSV file: xf-e193-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E193 (10.22%)
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3667 0.08710 0.08360 -0.0403 1.0000 0.0173
-8.750 -0.3649 0.08449 0.08104 -0.0405 1.0000 0.0170
-8.500 -0.3669 0.08127 0.07788 -0.0411 1.0000 0.0167
-8.250 -0.3716 0.07804 0.07472 -0.0416 1.0000 0.0165
-8.000 -0.3806 0.07494 0.07171 -0.0417 1.0000 0.0162
-7.750 -0.3869 0.07103 0.06788 -0.0440 0.9951 0.0159
-7.500 -0.3707 0.06257 0.05938 -0.0565 0.9784 0.0155
-7.250 -0.3556 0.05117 0.04777 -0.0701 0.9596 0.0148
-7.000 -0.3502 0.03749 0.03338 -0.0790 0.9370 0.0141
-6.750 -0.3294 0.03249 0.02785 -0.0818 0.9210 0.0144
-6.500 -0.3054 0.02909 0.02397 -0.0834 0.9056 0.0152
-6.250 -0.2815 0.02582 0.02011 -0.0841 0.8899 0.0156
-6.000 -0.2572 0.02314 0.01689 -0.0842 0.8746 0.0157
-5.750 -0.2322 0.02108 0.01436 -0.0839 0.8595 0.0158
-5.500 -0.2070 0.01950 0.01239 -0.0835 0.8448 0.0160
-5.250 -0.1818 0.01822 0.01081 -0.0830 0.8307 0.0163
-5.000 -0.1566 0.01717 0.00952 -0.0824 0.8175 0.0166
-4.750 -0.1314 0.01630 0.00844 -0.0818 0.8050 0.0171
-4.500 -0.1062 0.01554 0.00752 -0.0813 0.7933 0.0176
-4.250 -0.0813 0.01482 0.00667 -0.0807 0.7823 0.0186
-4.000 -0.0556 0.01438 0.00614 -0.0804 0.7714 0.0205
-3.750 -0.0296 0.01395 0.00556 -0.0799 0.7615 0.0225
-3.500 -0.0038 0.01348 0.00497 -0.0795 0.7523 0.0245
-3.250 0.0226 0.01312 0.00449 -0.0791 0.7430 0.0284
-3.000 0.0486 0.01268 0.00406 -0.0787 0.7347 0.0429
-2.750 0.0745 0.01227 0.00376 -0.0784 0.7262 0.0829
-2.500 0.1003 0.01188 0.00355 -0.0782 0.7187 0.1398
-2.250 0.1261 0.01154 0.00339 -0.0780 0.7109 0.2046
-2.000 0.1517 0.01120 0.00327 -0.0778 0.7039 0.2809
-1.750 0.1774 0.01091 0.00316 -0.0775 0.6967 0.3547
-1.500 0.2025 0.01061 0.00308 -0.0770 0.6903 0.4403
-1.250 0.2268 0.01028 0.00305 -0.0763 0.6833 0.5385
-1.000 0.2502 0.00997 0.00302 -0.0752 0.6777 0.6422
-0.750 0.2727 0.00964 0.00304 -0.0736 0.6710 0.7586
-0.500 0.3109 0.00942 0.00303 -0.0750 0.6651 0.9002
-0.250 0.3605 0.00941 0.00293 -0.0794 0.6590 0.9753
0.000 0.4025 0.00944 0.00285 -0.0825 0.6525 1.0000
0.250 0.4275 0.00954 0.00282 -0.0820 0.6473 1.0000
0.500 0.4526 0.00962 0.00284 -0.0814 0.6410 1.0000
0.750 0.4779 0.00973 0.00285 -0.0809 0.6354 1.0000
1.000 0.5033 0.00983 0.00289 -0.0804 0.6299 1.0000
1.250 0.5288 0.00993 0.00295 -0.0800 0.6240 1.0000
1.500 0.5545 0.01006 0.00299 -0.0796 0.6190 1.0000
1.750 0.5803 0.01016 0.00308 -0.0792 0.6130 1.0000
2.000 0.6061 0.01028 0.00317 -0.0788 0.6074 1.0000
2.250 0.6320 0.01041 0.00326 -0.0784 0.6023 1.0000
2.500 0.6579 0.01053 0.00339 -0.0780 0.5961 1.0000
2.750 0.6839 0.01066 0.00350 -0.0776 0.5905 1.0000
3.000 0.7098 0.01080 0.00364 -0.0773 0.5844 1.0000
3.250 0.7357 0.01092 0.00378 -0.0769 0.5776 1.0000
3.500 0.7615 0.01106 0.00392 -0.0765 0.5707 1.0000
3.750 0.7871 0.01119 0.00407 -0.0761 0.5627 1.0000
4.000 0.8127 0.01132 0.00424 -0.0756 0.5544 1.0000
4.250 0.8381 0.01145 0.00437 -0.0751 0.5457 1.0000
4.500 0.8634 0.01158 0.00456 -0.0747 0.5356 1.0000
4.750 0.8886 0.01173 0.00473 -0.0741 0.5251 1.0000
5.000 0.9135 0.01188 0.00492 -0.0736 0.5141 1.0000
5.250 0.9382 0.01204 0.00511 -0.0730 0.5020 1.0000
5.500 0.9626 0.01220 0.00533 -0.0723 0.4884 1.0000
5.750 0.9867 0.01239 0.00557 -0.0716 0.4734 1.0000
6.000 1.0103 0.01261 0.00582 -0.0709 0.4558 1.0000
6.250 1.0331 0.01286 0.00608 -0.0700 0.4329 1.0000
6.500 1.0529 0.01325 0.00635 -0.0686 0.3936 1.0000
6.750 1.0673 0.01399 0.00678 -0.0665 0.3283 1.0000
7.000 1.0780 0.01510 0.00747 -0.0640 0.2558 1.0000
7.250 1.0909 0.01612 0.00823 -0.0619 0.2045 1.0000
7.500 1.1034 0.01717 0.00904 -0.0599 0.1596 1.0000
7.750 1.1164 0.01816 0.00984 -0.0579 0.1232 1.0000
8.000 1.1275 0.01923 0.01072 -0.0557 0.0887 1.0000
8.250 1.1384 0.02027 0.01163 -0.0535 0.0618 1.0000
8.500 1.1455 0.02146 0.01265 -0.0507 0.0375 1.0000
8.750 1.1531 0.02249 0.01365 -0.0480 0.0254 1.0000
9.000 1.1608 0.02355 0.01473 -0.0453 0.0196 1.0000
9.500 1.1772 0.02577 0.01709 -0.0407 0.0157 1.0000
9.750 1.1857 0.02693 0.01837 -0.0386 0.0149 1.0000
10.000 1.1925 0.02827 0.01983 -0.0367 0.0141 1.0000
10.250 1.1986 0.02972 0.02139 -0.0349 0.0136 1.0000
10.500 1.2019 0.03150 0.02327 -0.0332 0.0130 1.0000
10.750 1.2057 0.03331 0.02519 -0.0317 0.0126 1.0000
11.000 1.2104 0.03514 0.02715 -0.0304 0.0122 1.0000
11.250 1.2156 0.03699 0.02912 -0.0293 0.0116 1.0000
11.500 1.2200 0.03899 0.03124 -0.0284 0.0112 1.0000
11.750 1.2226 0.04124 0.03360 -0.0275 0.0109 1.0000
12.000 1.2254 0.04352 0.03602 -0.0267 0.0107 1.0000
12.250 1.2278 0.04593 0.03854 -0.0260 0.0105 1.0000
12.500 1.2301 0.04840 0.04112 -0.0255 0.0103 1.0000
12.750 1.2321 0.05096 0.04378 -0.0250 0.0101 1.0000
13.000 1.2338 0.05362 0.04656 -0.0246 0.0100 1.0000
13.250 1.2352 0.05638 0.04942 -0.0243 0.0098 1.0000
13.500 1.2369 0.05917 0.05233 -0.0240 0.0097 1.0000
13.750 1.2378 0.06216 0.05543 -0.0237 0.0095 1.0000
14.000 1.2386 0.06529 0.05870 -0.0235 0.0094 1.0000
14.250 1.2399 0.06838 0.06193 -0.0235 0.0094 1.0000
14.500 1.2390 0.07189 0.06562 -0.0238 0.0093 1.0000
14.750 1.2372 0.07560 0.06954 -0.0243 0.0093 1.0000
15.000 1.2335 0.07968 0.07382 -0.0252 0.0092 1.0000
15.250 1.2278 0.08418 0.07853 -0.0265 0.0092 1.0000
15.500 1.2215 0.08893 0.08348 -0.0280 0.0092 1.0000
15.750 1.2128 0.09423 0.08899 -0.0300 0.0091 1.0000
16.000 1.2023 0.10002 0.09499 -0.0325 0.0091 1.0000
16.250 1.1913 0.10614 0.10132 -0.0354 0.0091 1.0000
16.500 1.1784 0.11291 0.10830 -0.0389 0.0091 1.0000
16.750 1.1655 0.11996 0.11554 -0.0428 0.0091 1.0000
17.000 1.1528 0.12723 0.12299 -0.0470 0.0092 1.0000
17.250 1.1386 0.13525 0.13118 -0.0518 0.0092 1.0000
17.500 1.1230 0.14403 0.14014 -0.0574 0.0092 1.0000
17.750 1.1083 0.15304 0.14930 -0.0631 0.0093 1.0000
18.000 1.0925 0.16285 0.15925 -0.0694 0.0093 1.0000
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Polar data table (+)
Polar graphs
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