WACO COOTIE AIRFOIL (cootie-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: WACO COOTIE AIRFOIL (cootie-il) Reynolds number: 200,000 Max Cl/Cd: 83.43 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cootie-il-200000-n5.txt Download as CSV file: xf-cootie-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WACO COOTIE 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2907 0.10887 0.10544 -0.0369 1.0000 0.0226
-9.500 -0.2929 0.10652 0.10315 -0.0374 1.0000 0.0227
-9.250 -0.2883 0.10333 0.10000 -0.0399 0.9956 0.0227
-8.750 -0.2587 0.09461 0.09128 -0.0430 0.9841 0.0236
-8.500 -0.2436 0.09113 0.08780 -0.0459 0.9759 0.0242
-8.250 -0.2297 0.08763 0.08429 -0.0494 0.9658 0.0247
-8.000 -0.2164 0.08396 0.08062 -0.0533 0.9552 0.0250
-7.750 -0.1929 0.08029 0.07691 -0.0654 0.9425 0.0298
-7.500 -0.1706 0.07569 0.07225 -0.0728 0.9342 0.0300
-7.250 -0.1521 0.07137 0.06788 -0.0772 0.9254 0.0300
-7.000 -0.1428 0.06798 0.06446 -0.0754 0.9197 0.0289
-6.750 -0.1259 0.06414 0.06058 -0.0786 0.9110 0.0277
-6.500 -0.0906 0.05734 0.05358 -0.0909 0.9029 0.0305
-6.250 -0.0746 0.05762 0.05386 -0.0894 0.8955 0.0387
-6.000 -0.0578 0.05372 0.04990 -0.0908 0.8890 0.0344
-5.750 -0.0224 0.04569 0.04156 -0.1001 0.8811 0.0313
-5.500 -0.0025 0.04508 0.04092 -0.0998 0.8748 0.0339
-5.250 0.0257 0.04154 0.03720 -0.1031 0.8671 0.0352
-4.750 0.0856 0.03343 0.02851 -0.1089 0.8533 0.0350
-4.500 0.1156 0.02998 0.02470 -0.1107 0.8471 0.0366
-4.250 0.1450 0.02648 0.02082 -0.1120 0.8394 0.0365
-4.000 0.1745 0.02304 0.01689 -0.1130 0.8328 0.0367
-3.750 0.2036 0.02015 0.01349 -0.1136 0.8251 0.0378
-3.500 0.2321 0.01831 0.01118 -0.1138 0.8179 0.0385
-3.250 0.2601 0.01694 0.00947 -0.1138 0.8092 0.0386
-3.000 0.2881 0.01593 0.00817 -0.1137 0.8016 0.0388
-2.750 0.3158 0.01515 0.00720 -0.1136 0.7917 0.0392
-2.500 0.3434 0.01453 0.00641 -0.1135 0.7826 0.0395
-2.250 0.3709 0.01391 0.00566 -0.1133 0.7722 0.0401
-2.000 0.3980 0.01340 0.00505 -0.1130 0.7587 0.0410
-1.750 0.4250 0.01303 0.00460 -0.1127 0.7436 0.0424
-1.500 0.4521 0.01278 0.00427 -0.1125 0.7284 0.0447
-1.000 0.5070 0.01238 0.00372 -0.1121 0.7024 0.0475
-0.750 0.5345 0.01224 0.00351 -0.1120 0.6902 0.0491
-0.500 0.5620 0.01215 0.00338 -0.1119 0.6787 0.0528
-0.250 0.5894 0.01211 0.00334 -0.1117 0.6675 0.0635
0.000 0.6168 0.01214 0.00334 -0.1116 0.6565 0.0837
0.250 0.6442 0.01220 0.00335 -0.1115 0.6465 0.0970
0.500 0.6715 0.01227 0.00335 -0.1114 0.6369 0.1056
0.750 0.6987 0.01235 0.00338 -0.1113 0.6269 0.1153
1.000 0.7259 0.01240 0.00343 -0.1112 0.6174 0.1255
1.250 0.7531 0.01246 0.00347 -0.1112 0.6086 0.1353
1.500 0.7803 0.01249 0.00354 -0.1112 0.5994 0.1504
1.750 0.8072 0.01249 0.00361 -0.1111 0.5904 0.1793
2.250 0.8563 0.01117 0.00384 -0.1098 0.5714 1.0000
2.500 0.8830 0.01136 0.00395 -0.1097 0.5621 1.0000
2.750 0.9099 0.01153 0.00409 -0.1096 0.5519 1.0000
3.000 0.9364 0.01171 0.00423 -0.1094 0.5413 1.0000
3.250 0.9627 0.01190 0.00439 -0.1092 0.5302 1.0000
3.500 0.9887 0.01211 0.00455 -0.1090 0.5172 1.0000
3.750 1.0144 0.01232 0.00473 -0.1087 0.5026 1.0000
4.000 1.0397 0.01255 0.00492 -0.1083 0.4870 1.0000
4.250 1.0649 0.01280 0.00515 -0.1080 0.4715 1.0000
4.500 1.0900 0.01307 0.00539 -0.1076 0.4571 1.0000
4.750 1.1146 0.01336 0.00565 -0.1072 0.4412 1.0000
5.000 1.1386 0.01369 0.00596 -0.1067 0.4228 1.0000
5.250 1.1619 0.01407 0.00627 -0.1061 0.4036 1.0000
5.500 1.1841 0.01452 0.00663 -0.1053 0.3815 1.0000
5.750 1.2057 0.01500 0.00702 -0.1045 0.3576 1.0000
6.000 1.2272 0.01550 0.00746 -0.1036 0.3368 1.0000
6.250 1.2489 0.01598 0.00791 -0.1028 0.3169 1.0000
6.500 1.2701 0.01649 0.00838 -0.1020 0.2974 1.0000
6.750 1.2890 0.01714 0.00891 -0.1008 0.2658 1.0000
7.000 1.3045 0.01804 0.00959 -0.0992 0.2143 1.0000
7.250 1.3122 0.01959 0.01066 -0.0966 0.1439 1.0000
7.500 1.3162 0.02142 0.01204 -0.0936 0.0826 1.0000
7.750 1.3291 0.02244 0.01300 -0.0916 0.0618 1.0000
8.000 1.3313 0.02403 0.01433 -0.0881 0.0237 1.0000
8.250 1.3392 0.02517 0.01550 -0.0853 0.0202 1.0000
8.500 1.3480 0.02630 0.01673 -0.0828 0.0177 1.0000
8.750 1.3583 0.02738 0.01798 -0.0807 0.0165 1.0000
9.000 1.3670 0.02861 0.01936 -0.0786 0.0155 1.0000
9.250 1.3743 0.02999 0.02090 -0.0765 0.0148 1.0000
9.500 1.3801 0.03157 0.02262 -0.0744 0.0142 1.0000
9.750 1.3841 0.03335 0.02455 -0.0723 0.0137 1.0000
10.000 1.3856 0.03542 0.02678 -0.0703 0.0132 1.0000
10.250 1.3836 0.03791 0.02942 -0.0683 0.0126 1.0000
10.500 1.3773 0.04093 0.03259 -0.0664 0.0121 1.0000
10.750 1.3783 0.04335 0.03512 -0.0651 0.0118 1.0000
11.000 1.3807 0.04570 0.03764 -0.0640 0.0114 1.0000
11.250 1.3805 0.04840 0.04047 -0.0630 0.0111 1.0000
11.500 1.3793 0.05131 0.04350 -0.0621 0.0109 1.0000
11.750 1.3778 0.05430 0.04662 -0.0614 0.0106 1.0000
12.000 1.3761 0.05738 0.04982 -0.0607 0.0104 1.0000
12.250 1.3747 0.06049 0.05304 -0.0601 0.0102 1.0000
12.500 1.3736 0.06360 0.05627 -0.0596 0.0100 1.0000
12.750 1.3730 0.06670 0.05947 -0.0591 0.0099 1.0000
13.000 1.3728 0.06978 0.06267 -0.0586 0.0097 1.0000
13.250 1.3730 0.07285 0.06584 -0.0582 0.0095 1.0000
13.500 1.3734 0.07594 0.06904 -0.0579 0.0093 1.0000
13.750 1.3736 0.07907 0.07230 -0.0576 0.0091 1.0000
14.000 1.3735 0.08227 0.07559 -0.0575 0.0089 1.0000
14.250 1.3736 0.08542 0.07879 -0.0573 0.0086 1.0000
14.500 1.3763 0.08799 0.08140 -0.0559 0.0083 1.0000
14.750 1.3724 0.09210 0.08571 -0.0568 0.0081 1.0000
15.000 1.3681 0.09638 0.09020 -0.0579 0.0080 1.0000
15.250 1.3638 0.10073 0.09474 -0.0590 0.0079 1.0000
15.500 1.3589 0.10526 0.09948 -0.0603 0.0078 1.0000
15.750 1.3528 0.11008 0.10449 -0.0618 0.0077 1.0000
16.000 1.3458 0.11519 0.10980 -0.0637 0.0077 1.0000
16.250 1.3379 0.12063 0.11544 -0.0659 0.0076 1.0000
16.500 1.3292 0.12641 0.12142 -0.0686 0.0076 1.0000
16.750 1.3200 0.13248 0.12768 -0.0717 0.0075 1.0000
17.000 1.3103 0.13889 0.13429 -0.0752 0.0075 1.0000
17.250 1.3000 0.14566 0.14125 -0.0791 0.0075 1.0000
17.500 1.2892 0.15278 0.14855 -0.0834 0.0075 1.0000
17.750 1.2784 0.16020 0.15615 -0.0881 0.0075 1.0000
18.000 1.2671 0.16815 0.16427 -0.0933 0.0076 1.0000
18.250 1.2556 0.17653 0.17281 -0.0988 0.0076 1.0000
18.500 1.2437 0.18552 0.18195 -0.1049 0.0076 1.0000
18.750 1.2320 0.19507 0.19164 -0.1113 0.0077 1.0000
19.000 1.2195 0.20576 0.20245 -0.1183 0.0078 1.0000
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