CLARK YH AIRFOIL (clarkyh-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK YH AIRFOIL (clarkyh-il) Reynolds number: 200,000 Max Cl/Cd: 62.27 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkyh-il-200000-n5.txt Download as CSV file: xf-clarkyh-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK YH 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.8997 0.05559 0.05179 -0.0480 1.0000 0.0215
-13.750 -0.9341 0.04645 0.04230 -0.0560 1.0000 0.0212
-13.500 -0.9523 0.04216 0.03773 -0.0561 1.0000 0.0215
-13.250 -0.9636 0.03895 0.03421 -0.0542 1.0000 0.0219
-13.000 -0.9660 0.03613 0.03109 -0.0524 1.0000 0.0226
-12.750 -0.9549 0.03483 0.02972 -0.0510 1.0000 0.0232
-12.500 -0.9409 0.03370 0.02849 -0.0498 1.0000 0.0240
-12.250 -0.9261 0.03255 0.02721 -0.0486 1.0000 0.0250
-12.000 -0.9123 0.03107 0.02548 -0.0473 1.0000 0.0264
-11.750 -0.8990 0.02931 0.02342 -0.0458 1.0000 0.0279
-11.500 -0.8787 0.02885 0.02296 -0.0448 1.0000 0.0290
-11.250 -0.8585 0.02831 0.02234 -0.0438 1.0000 0.0304
-11.000 -0.8397 0.02742 0.02128 -0.0426 1.0000 0.0322
-10.750 -0.8225 0.02617 0.01971 -0.0411 1.0000 0.0345
-10.500 -0.8039 0.02572 0.01925 -0.0397 1.0000 0.0358
-10.250 -0.7806 0.02524 0.01868 -0.0392 0.9943 0.0377
-10.000 -0.7500 0.02443 0.01762 -0.0401 0.9827 0.0407
-9.750 -0.7202 0.02354 0.01643 -0.0408 0.9731 0.0432
-9.500 -0.6918 0.02278 0.01566 -0.0413 0.9643 0.0453
-9.250 -0.6628 0.02211 0.01486 -0.0417 0.9562 0.0479
-9.000 -0.6347 0.02148 0.01399 -0.0417 0.9473 0.0505
-8.750 -0.6081 0.02072 0.01305 -0.0415 0.9382 0.0525
-8.500 -0.5825 0.01987 0.01219 -0.0411 0.9292 0.0548
-8.250 -0.5578 0.01928 0.01151 -0.0404 0.9194 0.0569
-8.000 -0.5330 0.01874 0.01084 -0.0396 0.9101 0.0591
-7.750 -0.5087 0.01823 0.01019 -0.0386 0.8999 0.0607
-7.500 -0.4851 0.01757 0.00947 -0.0376 0.8909 0.0624
-7.250 -0.4617 0.01701 0.00888 -0.0365 0.8817 0.0643
-7.000 -0.4376 0.01656 0.00837 -0.0355 0.8721 0.0660
-6.750 -0.4138 0.01615 0.00787 -0.0344 0.8629 0.0675
-6.500 -0.3890 0.01576 0.00741 -0.0335 0.8530 0.0691
-6.250 -0.3642 0.01542 0.00698 -0.0326 0.8448 0.0710
-6.000 -0.3393 0.01505 0.00660 -0.0318 0.8357 0.0731
-5.750 -0.3140 0.01474 0.00625 -0.0311 0.8274 0.0752
-5.500 -0.2883 0.01447 0.00593 -0.0304 0.8184 0.0778
-5.250 -0.2624 0.01421 0.00562 -0.0297 0.8094 0.0810
-5.000 -0.2366 0.01395 0.00532 -0.0291 0.8002 0.0857
-4.750 -0.2102 0.01373 0.00505 -0.0285 0.7897 0.0931
-4.500 -0.1845 0.01345 0.00475 -0.0279 0.7793 0.1026
-4.250 -0.1587 0.01315 0.00444 -0.0272 0.7676 0.1143
-4.000 -0.1332 0.01282 0.00419 -0.0266 0.7548 0.1312
-3.750 -0.1075 0.01258 0.00412 -0.0261 0.7415 0.1752
-3.500 -0.0807 0.01249 0.00399 -0.0257 0.7277 0.1968
-3.250 -0.0539 0.01241 0.00383 -0.0252 0.7133 0.2089
-3.000 -0.0275 0.01232 0.00367 -0.0247 0.6977 0.2181
-2.750 -0.0012 0.01224 0.00351 -0.0242 0.6816 0.2265
-2.500 0.0251 0.01218 0.00336 -0.0237 0.6661 0.2342
-2.250 0.0512 0.01213 0.00324 -0.0232 0.6513 0.2429
-2.000 0.0773 0.01210 0.00313 -0.0227 0.6376 0.2528
-1.750 0.1034 0.01205 0.00305 -0.0222 0.6241 0.2626
-1.500 0.1296 0.01201 0.00299 -0.0219 0.6113 0.2744
-1.250 0.1556 0.01195 0.00295 -0.0215 0.6004 0.2910
-1.000 0.1812 0.01185 0.00292 -0.0210 0.5902 0.3189
-0.750 0.2059 0.01162 0.00291 -0.0205 0.5797 0.3798
-0.500 0.2245 0.01097 0.00287 -0.0188 0.5704 0.5526
-0.250 0.2657 0.01028 0.00322 -0.0206 0.5585 0.8829
0.000 0.3174 0.01047 0.00340 -0.0253 0.5453 0.9240
0.250 0.3553 0.01064 0.00352 -0.0272 0.5350 0.9449
0.500 0.3926 0.01084 0.00366 -0.0290 0.5252 0.9636
0.750 0.4307 0.01099 0.00377 -0.0312 0.5149 0.9761
1.000 0.4687 0.01113 0.00385 -0.0334 0.5039 0.9852
1.250 0.5096 0.01125 0.00390 -0.0364 0.4913 0.9924
1.500 0.5476 0.01134 0.00394 -0.0387 0.4803 0.9971
1.750 0.5813 0.01143 0.00401 -0.0402 0.4713 1.0000
2.000 0.6060 0.01155 0.00409 -0.0398 0.4627 1.0000
2.250 0.6306 0.01168 0.00419 -0.0394 0.4525 1.0000
2.500 0.6548 0.01183 0.00430 -0.0389 0.4424 1.0000
2.750 0.6789 0.01199 0.00442 -0.0384 0.4305 1.0000
3.000 0.7028 0.01215 0.00457 -0.0379 0.4177 1.0000
3.250 0.7267 0.01232 0.00473 -0.0374 0.4064 1.0000
3.500 0.7502 0.01252 0.00490 -0.0368 0.3945 1.0000
3.750 0.7739 0.01270 0.00509 -0.0362 0.3799 1.0000
4.000 0.7971 0.01290 0.00529 -0.0356 0.3612 1.0000
4.250 0.8195 0.01316 0.00550 -0.0349 0.3310 1.0000
4.500 0.8390 0.01365 0.00575 -0.0338 0.2827 1.0000
4.750 0.8582 0.01420 0.00613 -0.0327 0.2583 1.0000
5.000 0.8788 0.01463 0.00652 -0.0318 0.2470 1.0000
5.250 0.8994 0.01504 0.00692 -0.0309 0.2397 1.0000
5.500 0.9205 0.01540 0.00732 -0.0300 0.2340 1.0000
5.750 0.9404 0.01585 0.00776 -0.0289 0.2274 1.0000
6.000 0.9605 0.01627 0.00820 -0.0279 0.2198 1.0000
6.250 0.9794 0.01676 0.00868 -0.0268 0.2110 1.0000
6.500 0.9995 0.01715 0.00912 -0.0258 0.2032 1.0000
6.750 1.0183 0.01761 0.00959 -0.0247 0.1945 1.0000
7.000 1.0383 0.01798 0.01002 -0.0238 0.1846 1.0000
7.250 1.0571 0.01840 0.01048 -0.0227 0.1729 1.0000
7.500 1.0760 0.01881 0.01092 -0.0216 0.1585 1.0000
7.750 1.0930 0.01933 0.01138 -0.0203 0.1315 1.0000
8.000 1.1002 0.02051 0.01221 -0.0179 0.0898 1.0000
8.250 1.1102 0.02151 0.01314 -0.0158 0.0757 1.0000
8.500 1.1210 0.02243 0.01409 -0.0138 0.0632 1.0000
8.750 1.1290 0.02342 0.01505 -0.0114 0.0472 1.0000
9.000 1.1337 0.02455 0.01609 -0.0088 0.0377 1.0000
9.250 1.1394 0.02571 0.01727 -0.0066 0.0332 1.0000
9.500 1.1440 0.02708 0.01867 -0.0046 0.0300 1.0000
9.750 1.1513 0.02835 0.02006 -0.0031 0.0283 1.0000
10.000 1.1572 0.02981 0.02165 -0.0017 0.0266 1.0000
10.250 1.1611 0.03152 0.02344 -0.0005 0.0252 1.0000
10.500 1.1621 0.03357 0.02558 0.0006 0.0240 1.0000
10.750 1.1622 0.03583 0.02794 0.0015 0.0230 1.0000
11.000 1.1657 0.03789 0.03012 0.0021 0.0223 1.0000
11.250 1.1677 0.04019 0.03254 0.0025 0.0216 1.0000
11.500 1.1689 0.04267 0.03514 0.0027 0.0209 1.0000
11.750 1.1694 0.04532 0.03789 0.0027 0.0202 1.0000
12.000 1.1691 0.04813 0.04080 0.0025 0.0196 1.0000
12.250 1.1675 0.05115 0.04392 0.0023 0.0191 1.0000
12.500 1.1639 0.05444 0.04729 0.0019 0.0186 1.0000
12.750 1.1583 0.05797 0.05088 0.0016 0.0182 1.0000
13.000 1.1586 0.06096 0.05401 0.0011 0.0178 1.0000
13.250 1.1579 0.06413 0.05731 0.0005 0.0174 1.0000
13.500 1.1565 0.06744 0.06073 -0.0001 0.0170 1.0000
13.750 1.1548 0.07086 0.06426 -0.0008 0.0167 1.0000
14.000 1.1529 0.07436 0.06787 -0.0016 0.0164 1.0000
14.250 1.1509 0.07793 0.07154 -0.0025 0.0161 1.0000
14.500 1.1486 0.08160 0.07530 -0.0034 0.0158 1.0000
14.750 1.1461 0.08537 0.07917 -0.0046 0.0155 1.0000
15.000 1.1436 0.08920 0.08308 -0.0058 0.0152 1.0000
15.250 1.1410 0.09305 0.08699 -0.0070 0.0149 1.0000
15.500 1.1386 0.09685 0.09087 -0.0082 0.0147 1.0000
15.750 1.1360 0.10069 0.09477 -0.0093 0.0144 1.0000
16.000 1.1310 0.10530 0.09955 -0.0111 0.0142 1.0000
16.250 1.1253 0.11009 0.10451 -0.0131 0.0140 1.0000
16.500 1.1191 0.11508 0.10964 -0.0152 0.0137 1.0000
16.750 1.1125 0.12023 0.11495 -0.0174 0.0135 1.0000
17.000 1.1053 0.12564 0.12050 -0.0199 0.0134 1.0000
17.250 1.0974 0.13130 0.12632 -0.0226 0.0133 1.0000
17.500 1.0885 0.13734 0.13251 -0.0257 0.0131 1.0000
17.750 1.0786 0.14383 0.13915 -0.0290 0.0130 1.0000
18.000 1.0670 0.15094 0.14643 -0.0329 0.0130 1.0000
18.250 1.0532 0.15887 0.15452 -0.0372 0.0129 1.0000
18.500 1.0346 0.16846 0.16429 -0.0425 0.0130 1.0000
18.750 1.0008 0.18325 0.17931 -0.0503 0.0131 1.0000
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