TH 25816 HALE AIRFOIL (th25816-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: TH 25816 HALE AIRFOIL (th25816-il) Reynolds number: 200,000 Max Cl/Cd: 19.13 at α=13.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-th25816-il-200000-n5.txt Download as CSV file: xf-th25816-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: TH 25816 HALE 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
------ -------- --------- --------- -------- -------- --------
-17.750 -0.3590 0.09729 0.09194 -0.1703 0.9238 0.0201
-17.250 -0.4117 0.08733 0.08167 -0.1698 0.9150 0.0200
-17.000 -0.4316 0.08172 0.07583 -0.1717 0.9129 0.0200
-16.750 -0.4420 0.07721 0.07111 -0.1735 0.9115 0.0200
-16.500 -0.4516 0.07279 0.06646 -0.1751 0.9104 0.0201
-16.250 -0.4744 0.07079 0.06439 -0.1705 0.9025 0.0202
-16.000 -0.4795 0.06770 0.06112 -0.1705 0.9000 0.0202
-15.750 -0.4778 0.06488 0.05816 -0.1711 0.8985 0.0203
-15.500 -0.4733 0.06223 0.05537 -0.1719 0.8973 0.0205
-15.250 -0.4912 0.06097 0.05405 -0.1668 0.8889 0.0206
-15.000 -0.4873 0.05868 0.05159 -0.1665 0.8865 0.0206
-14.750 -0.4785 0.05660 0.04939 -0.1669 0.8849 0.0208
-14.500 -0.4669 0.05459 0.04726 -0.1674 0.8838 0.0210
-14.250 -0.4808 0.05375 0.04634 -0.1623 0.8750 0.0211
-14.000 -0.4699 0.05209 0.04457 -0.1620 0.8729 0.0213
-13.750 -0.4559 0.05048 0.04283 -0.1622 0.8714 0.0216
-13.500 -0.4390 0.04895 0.04118 -0.1626 0.8703 0.0218
-13.250 -0.4461 0.04834 0.04051 -0.1580 0.8622 0.0219
-13.000 -0.4317 0.04705 0.03911 -0.1577 0.8599 0.0223
-12.750 -0.4131 0.04581 0.03777 -0.1578 0.8583 0.0226
-12.500 -0.3941 0.04459 0.03645 -0.1580 0.8570 0.0230
-12.250 -0.3736 0.04342 0.03515 -0.1584 0.8560 0.0235
-12.000 -0.3785 0.04311 0.03478 -0.1538 0.8482 0.0238
-11.750 -0.3620 0.04212 0.03375 -0.1533 0.8460 0.0243
-11.500 -0.3435 0.04106 0.03268 -0.1533 0.8444 0.0247
-11.250 -0.3242 0.03997 0.03157 -0.1535 0.8430 0.0253
-11.000 -0.3038 0.03886 0.03041 -0.1538 0.8419 0.0258
-10.750 -0.3041 0.03848 0.03000 -0.1501 0.8357 0.0260
-10.500 -0.2927 0.03767 0.02913 -0.1486 0.8325 0.0265
-10.250 -0.2769 0.03671 0.02812 -0.1481 0.8305 0.0271
-10.000 -0.2596 0.03569 0.02703 -0.1479 0.8290 0.0276
-9.750 -0.2406 0.03464 0.02589 -0.1479 0.8277 0.0282
-9.500 -0.2220 0.03345 0.02468 -0.1481 0.8266 0.0289
-9.250 -0.2309 0.03330 0.02450 -0.1426 0.8193 0.0293
-9.000 -0.2198 0.03254 0.02370 -0.1411 0.8163 0.0299
-8.750 -0.2039 0.03168 0.02278 -0.1404 0.8144 0.0311
-8.500 -0.1849 0.03084 0.02186 -0.1403 0.8128 0.0329
-8.250 -0.1657 0.02988 0.02088 -0.1403 0.8115 0.0348
-7.750 -0.1661 0.02935 0.02028 -0.1321 0.8017 0.0377
-7.500 -0.1534 0.02867 0.01956 -0.1306 0.7991 0.0407
-7.250 -0.1363 0.02791 0.01878 -0.1299 0.7972 0.0456
-7.000 -0.1198 0.02704 0.01793 -0.1292 0.7957 0.0564
-6.750 -0.1046 0.02599 0.01701 -0.1285 0.7944 0.0835
-6.500 -0.1428 0.02678 0.01779 -0.1166 0.7851 0.0806
-6.250 -0.1429 0.02590 0.01708 -0.1128 0.7821 0.1184
-6.000 -0.1393 0.02484 0.01621 -0.1098 0.7800 0.1645
-5.750 -0.1416 0.02351 0.01517 -0.1059 0.7782 0.2298
-4.750 -0.2672 0.02420 0.01607 -0.0642 0.7516 0.2888
-4.500 -0.2867 0.02352 0.01552 -0.0560 0.7480 0.3269
-4.000 -0.3414 0.02343 0.01589 -0.0373 0.7352 0.4222
-3.750 -0.3481 0.02247 0.01562 -0.0314 0.7321 0.5508
-3.500 -0.3268 0.02226 0.01566 -0.0301 0.7307 0.6227
-3.250 -0.3023 0.02224 0.01571 -0.0294 0.7297 0.6682
-2.750 -0.2651 0.02338 0.01692 -0.0255 0.7252 0.7195
-2.500 -0.2165 0.02367 0.01716 -0.0286 0.7264 0.7268
-1.500 -0.2230 0.02720 0.02063 -0.0107 0.7008 0.7439
-1.250 -0.1991 0.02722 0.02057 -0.0106 0.6990 0.7468
-1.000 -0.1729 0.02706 0.02031 -0.0110 0.6978 0.7506
-0.750 -0.1449 0.02674 0.01988 -0.0117 0.6968 0.7547
-0.500 -0.1148 0.02666 0.01974 -0.0125 0.6960 0.7563
-0.250 -0.1098 0.02762 0.02070 -0.0093 0.6907 0.7585
0.000 -0.0675 0.02700 0.01999 -0.0121 0.6923 0.7605
0.250 -0.0270 0.02647 0.01938 -0.0146 0.6934 0.7629
1.250 0.0145 0.02900 0.02183 -0.0062 0.6758 0.7756
1.500 0.0536 0.02849 0.02126 -0.0083 0.6768 0.7776
3.500 0.1491 0.03411 0.02683 0.0050 0.6413 0.8041
3.750 0.1900 0.03333 0.02601 0.0027 0.6431 0.8066
4.000 0.2272 0.03274 0.02541 0.0010 0.6441 0.8082
5.000 0.2826 0.03531 0.02802 0.0062 0.6269 0.8210
5.500 0.2941 0.03749 0.03026 0.0109 0.6139 0.8266
6.000 0.3078 0.03961 0.03244 0.0151 0.6011 0.8323
6.250 0.3339 0.03957 0.03241 0.0147 0.5992 0.8354
6.500 0.3628 0.03940 0.03223 0.0138 0.5979 0.8390
6.750 0.3919 0.03913 0.03196 0.0131 0.5969 0.8417
7.000 0.4201 0.03883 0.03170 0.0127 0.5960 0.8438
7.250 0.4499 0.03846 0.03134 0.0121 0.5953 0.8461
8.250 0.4808 0.04265 0.03568 0.0190 0.5672 0.8589
8.500 0.5063 0.04240 0.03547 0.0191 0.5653 0.8610
8.750 0.5344 0.04201 0.03512 0.0187 0.5640 0.8634
9.000 0.5646 0.04152 0.03466 0.0180 0.5628 0.8661
9.250 0.5944 0.04112 0.03429 0.0172 0.5612 0.8689
9.750 0.6168 0.04284 0.03608 0.0195 0.5467 0.8750
10.000 0.6484 0.04213 0.03542 0.0188 0.5454 0.8770
10.500 0.6671 0.04378 0.03717 0.0221 0.5300 0.8824
10.750 0.6639 0.04566 0.03911 0.0247 0.5183 0.8855
11.000 0.6937 0.04522 0.03871 0.0239 0.5148 0.8882
11.250 0.7311 0.04432 0.03782 0.0221 0.5125 0.8907
11.500 0.7276 0.04607 0.03964 0.0250 0.4996 0.8929
11.750 0.7632 0.04502 0.03861 0.0239 0.4961 0.8953
12.000 0.7675 0.04631 0.03996 0.0258 0.4840 0.8980
12.250 0.8061 0.04514 0.03878 0.0243 0.4788 0.9006
12.500 0.8155 0.04620 0.03987 0.0254 0.4661 0.9032
12.750 0.8375 0.04637 0.04004 0.0253 0.4548 0.9056
13.000 0.8657 0.04580 0.03944 0.0249 0.4438 0.9078
13.250 0.8813 0.04620 0.03981 0.0257 0.4294 0.9103
13.500 0.8952 0.04680 0.04040 0.0266 0.4144 0.9127
13.750 0.9085 0.04750 0.04107 0.0274 0.3991 0.9153
14.000 0.9208 0.04832 0.04184 0.0282 0.3831 0.9178
14.250 0.9311 0.04935 0.04282 0.0291 0.3676 0.9202
14.500 0.9379 0.05049 0.04394 0.0305 0.3520 0.9224
14.750 0.9440 0.05173 0.04515 0.0319 0.3370 0.9247
15.000 0.9493 0.05312 0.04649 0.0332 0.3215 0.9272
15.250 0.9530 0.05472 0.04804 0.0345 0.3057 0.9296
15.500 0.9570 0.05637 0.04966 0.0356 0.2908 0.9319
15.750 0.9599 0.05815 0.05141 0.0367 0.2753 0.9341
16.000 0.9623 0.05997 0.05320 0.0378 0.2604 0.9363
16.250 0.9667 0.06172 0.05495 0.0386 0.2468 0.9385
16.500 0.9702 0.06361 0.05682 0.0394 0.2339 0.9406
16.750 0.9727 0.06561 0.05880 0.0401 0.2207 0.9429
17.000 0.9745 0.06773 0.06090 0.0408 0.2087 0.9452
17.250 0.9785 0.06975 0.06292 0.0412 0.1964 0.9472
17.500 0.9832 0.07177 0.06497 0.0414 0.1855 0.9491
17.750 0.9858 0.07405 0.06723 0.0415 0.1750 0.9510
18.000 0.9907 0.07615 0.06935 0.0415 0.1655 0.9529
18.250 0.9950 0.07834 0.07157 0.0415 0.1567 0.9552
18.500 0.9979 0.08069 0.07393 0.0414 0.1485 0.9576
18.750 1.0048 0.08280 0.07610 0.0409 0.1411 0.9599
19.000 1.0087 0.08533 0.07863 0.0403 0.1341 0.9620
19.250 1.0166 0.08749 0.08086 0.0394 0.1279 0.9643
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